Vacuum thermal environment simulation test system for spacecraft

Abstract

The application provides a vacuum thermal environment simulation test system for a spacecraft, comprising: a vacuum container; at least one xenon lamp optical assembly arranged in the vacuum container, the xenon lamp optical assembly comprising a sealed protective tank and a xenon lamp body arranged in the sealed protective tank, wherein the sealed protective tank is provided with an air inlet and an air outlet, the air inlet is used for introducing cooling gas into the sealed protective tank, and the air outlet is used for discharging the cooling gas flowing through the surface of the xenon lamp body out of the sealed protective tank; a simulation module used for simulating and determining configuration parameters of the xenon lamp optical assembly; and a control module used for controlling the operating state of the xenon lamp optical assembly according to the configuration parameters. The application realizes the direct arrangement and stable operation of the xenon lamp in the vacuum container, and provides an external heat flow simulation scheme for the spacecraft thermal test, which takes into account the spectral authenticity and structural simplicity.

Description

Technical Field

[0001] This application relates to the field of computer technology, and more specifically, to a vacuum thermal environment simulation test system for spacecraft. Background Technology

[0002] The space vacuum thermal environment is one of the main environmental factors affecting the reliability of spacecraft. In order to verify the overall function of spacecraft under on-orbit operation conditions, it is necessary to conduct simulated thermal tests on the ground.

[0003] Currently, two main types of external heat flux simulation methods are used in spacecraft thermal testing. One type is the incident heat flux simulation method, represented by solar simulators. This method can simulate the solar spectrum, collimation, and irradiance uniformity with high precision, and the experimental results are relatively ideal. However, due to its high system power and complex structure, it generally suffers from high cost and poor operational flexibility. The other type is the absorption heat flux simulation method, represented by infrared lamp arrays. This method only simulates the absorbed heat flux on the spacecraft surface. It has the advantages of simple structure and low cost, but its spectral characteristics differ significantly from the real sun, making it unsuitable for experimental scenarios with specific requirements for spectral characteristics.

[0004] Therefore, this application provides a vacuum thermal environment simulation test system for spacecraft to solve one of the aforementioned technical problems. Summary of the Invention

[0005] The purpose of this application is to provide a vacuum thermal environment simulation and testing system for spacecraft, which can solve at least one of the technical problems mentioned above. The specific solution is as follows: According to a specific embodiment of this application, this application provides a vacuum thermal environment simulation test system for spacecraft, the system comprising: A vacuum container used to house a spacecraft to be tested; At least one xenon lamp optical assembly is disposed inside the vacuum container for outputting simulated solar irradiation to the spacecraft under test; the xenon lamp optical assembly includes a sealed protective canister and a xenon lamp body disposed inside the sealed protective canister, wherein the sealed protective canister is provided with an air inlet and an air outlet, the air inlet is used to introduce cooling gas into the sealed protective canister, and the air outlet is used to discharge the cooling gas flowing over the surface of the xenon lamp body from the sealed protective canister; The simulation module is used to simulate and determine the configuration parameters of the xenon lamp optical component based on the optical parameters of the xenon lamp optical component, the configuration parameters being such that the light field emitted by the xenon lamp optical component meets the preset irradiance distribution requirements; A control module, connected to the xenon lamp optical component and the simulation module, is used to control the operating state of the xenon lamp optical component according to the configuration parameters.

[0006] In some possible embodiments, the sealed protective canister has a cylindrical structure, the xenon lamp body is arranged along the axial direction of the sealed protective canister, and the optical axis of the xenon lamp body is coaxial with the axis of the sealed protective canister. The xenon lamp optical assembly also includes a bowl-shaped condenser lens. The bottom of the condenser lens has a bottom through hole, and the xenon lamp body passes through the bottom through hole. The opening of the condenser lens faces the light-emitting end face of the sealed protective canister.

[0007] In some possible embodiments, the air inlet is located on the rear cover end face of the sealed protective canister, and a cold air channel is provided between the air inlet and the through hole at the bottom of the condenser lens. Cooling gas enters the bowl of the condenser lens through the cold air channel, flows through the surface of the xenon lamp body, and is discharged from the air outlet at the mouth of the bowl, and is discharged from the sealed protective canister through the air outlet.

[0008] In some possible embodiments, the configuration parameters include the surface profile parameters of the condenser lens, such that the light spot emitted by the condenser lens is square on the test surface of the spacecraft under test.

[0009] In some possible embodiments, the condenser lens adopts a non-intersecting optical path layout, and the rim of the condenser lens does not block light from the xenon lamp body.

[0010] In some possible embodiments, the configuration parameters include array arrangement parameters of the plurality of xenon lamp optical components, the array arrangement parameters including at least the spacing between adjacent xenon lamp optical components, the spacing being such that the edges of the light spots emitted by adjacent xenon lamp optical components overlap each other.

[0011] In some possible embodiments, the simulation module iterates using the irradiation uniformity of the test surface of the spacecraft under test as the target value and the spacing between adjacent xenon lamp optical components as the variable to determine the array arrangement parameters.

[0012] In some possible embodiments, the control module also stores a preset orbital period external heat flow variation curve, and the control module controls the output irradiance of the xenon lamp optical component according to the variation curve to simulate the time-varying characteristics of external heat flow during the spacecraft's on-orbit operation.

[0013] In some possible embodiments, the system further includes a high-voltage triggering module and a constant current drive power supply; The high-voltage triggering module is installed at the rear cover flange inside the sealed protective canister and is electrically connected to the xenon lamp body through a high-voltage wire passing through the rear cover flange. The high-voltage triggering module is used to apply a high-voltage pulse to the xenon lamp body to ignite the xenon lamp body. The constant current drive power supply is electrically connected to the xenon lamp body and is used to output a constant current to the xenon lamp body after the xenon lamp body is ignited.

[0014] In some possible embodiments, the system further includes an irradiance sensor disposed on the test surface of the spacecraft under test or on the light-emitting surface of the xenon lamp optical assembly, for collecting actual irradiance data and feeding it back to the control module; the control module adjusts the driving current of the xenon lamp body according to the comparison result of the actual irradiance data and the target irradiance value.

[0015] Compared with the prior art, the above-described solutions of this application have at least the following beneficial effects: By isolating the xenon lamp body from the internal environment of the vacuum container through a sealed protective canister, the pressure atmosphere inside the canister is maintained to allow for the convection of cooling gas. This solves the problem that xenon lamps cannot be cooled by air in a vacuum environment and are prone to high-voltage breakdown, allowing the xenon lamp to operate directly inside the vacuum container. At the same time, the simulation module determines the configuration parameters that meet the preset irradiance distribution requirements, and the control module controls the operating status according to the configuration parameters. This balances the accuracy of solar spectrum simulation with the simplicity of system structure, providing realistic, controllable and reliable external heat flow simulation conditions for spacecraft thermal experiments. Attached Figure Description

[0016] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with this application and, together with the description, serve to explain the principles of this application. It is obvious that the drawings described below are merely some embodiments of this application, and those skilled in the art can obtain other drawings based on these drawings without any inventive effort. In the drawings: Figure 1 This is a block diagram of a vacuum thermal environment simulation test system for spacecraft, as shown in an embodiment of this application. Figure 2 This is a schematic diagram of the xenon lamp optical components of a vacuum thermal environment simulation test system for spacecraft, as shown in an embodiment of this application. Figure 3 This is a schematic diagram of the internal structure of the xenon lamp optical components of a vacuum thermal environment simulation test system for spacecraft, as shown in an embodiment of this application. Figure 4 This is a schematic diagram of the xenon lamp body structure of a vacuum thermal environment simulation test system for spacecraft, as shown in an embodiment of this application. Figure 5 A schematic diagram of the xenon lamp body and condenser lens of a vacuum thermal environment simulation test system for spacecraft, as shown in an embodiment of this application. Figure 1 ; Figure 6A schematic diagram of the xenon lamp body and condenser lens of a vacuum thermal environment simulation test system for spacecraft, as shown in an embodiment of this application. Figure 2 ; Explanation of reference numerals in the attached figures: 1. Vacuum container; 2. Xenon lamp optical components; 21. Sealed protective container; 211. Air inlet; 212. Cold air channel; 213. Light-emitting end face; 214. Air outlet; 215. Rear cover end face; 22. Xenon lamp body; 221. Anode; 222. Cathode; 223. Bulb (light-emitting area); 23. Condenser lens; 231. Through hole at the bottom of the bowl; 232. Air outlet; 3. Simulation module; 4. Control module. Detailed Implementation

[0017] To make the objectives, technical solutions, and advantages of this application clearer, the application will be further described in detail below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0018] The terminology used in the embodiments of this application is for the purpose of describing particular embodiments only and is not intended to limit the application. The singular forms “a,” “said,” and “the” used in the embodiments of this application and the appended claims are also intended to include the plural forms, and “multiple” generally includes at least two unless the context clearly indicates otherwise.

[0019] It should be understood that the term "and / or" used in this article is merely a description of the relationship between related objects, indicating that three relationships can exist. For example, A and / or B can represent: A existing alone, A and B existing simultaneously, and B existing alone. Additionally, the character " / " in this article generally indicates that the preceding and following related objects have an "or" relationship.

[0020] It should be understood that although the terms first, second, third, etc., may be used in the embodiments of this application, these descriptions should not be limited to these terms. These terms are only used to distinguish the descriptions. For example, first may also be referred to as second without departing from the scope of the embodiments of this application, and similarly, second may also be referred to as first.

[0021] It should also be noted that the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that an article or device that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such an article or device. Without further limitation, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the article or device that includes said element.

[0022] The space vacuum thermal environment, composed of vacuum, cold black space, and external space heat flow, is one of the main environmental factors affecting spacecraft reliability and can lead to malfunctions in satellite instruments and equipment. Therefore, to verify the overall functionality of a spacecraft in orbit, thorough environmental simulation tests must be conducted on the ground, with thermal tests simulating space thermal environment conditions being the core component. External heat flow simulation is a key technology in this test, and its accuracy directly determines the temperature level and error range of the thermal balance test.

[0023] Currently, external heat flux simulation in spacecraft thermal testing mainly falls into two categories. One category is the incident heat flux simulation method, represented by solar simulators. While this method can accurately reproduce the sun's spectrum, collimation, and uniformity, it suffers from high system power and complex structure, resulting in high costs and insufficient operational flexibility. The other category is the absorption heat flux simulation method, represented by infrared lamps. This method only simulates the absorbed heat flux on the spacecraft surface, offering advantages such as simple structure and low cost, but it cannot match the true spectral characteristics of the sun. Therefore, both methods have their strengths in spectral accuracy and engineering simplicity, but also their significant drawbacks.

[0024] For specific experimental scenarios such as spacecraft solar panels and large components, there is an urgent engineering need for an external heat flow simulation method that is both easy to implement and can preserve the characteristics of the solar spectrum. However, existing systems have consistently failed to achieve both of these capabilities. To address this, this patent proposes an external heat flow simulation method based on a solar simulation lamp array. This method aims to combine the hyperspectral simulation performance of the incident method with the low cost and simple structure advantages of the absorption method, providing a more realistic and convenient heat flow simulation scheme for relevant spacecraft experiments.

[0025] The following is in conjunction with the appendix Figure 1-6 Detailed description of optional embodiments of the present invention.

[0026] like Figures 1 to 6 As shown in the figure, according to a specific embodiment of the present invention, the present invention provides a vacuum thermal environment simulation test system for spacecraft, the system comprising: Vacuum container 1, used to contain the spacecraft to be tested; At least one xenon lamp optical assembly 2 is disposed inside a vacuum container 1 for outputting simulated solar irradiation to the spacecraft under test; the xenon lamp optical assembly 2 includes a sealed protective container 21 and a xenon lamp body 22 disposed inside the sealed protective container 21, wherein the sealed protective container 21 is provided with an air inlet 211 and an air outlet 214, the air inlet 211 is used to introduce cooling gas into the sealed protective container 21, and the air outlet 214 is used to discharge the cooling gas flowing over the surface of the xenon lamp body 22 out of the sealed protective container 21; Simulation module 3 is used to simulate and determine the configuration parameters of xenon lamp optical component 2 based on the optical parameters of xenon lamp optical component 2. The configuration parameters make the light field emitted by xenon lamp optical component 2 meet the preset irradiance distribution requirements. The control module 4 is connected to the xenon lamp optical component 2 and the simulation module 3, and is used to control the operating status of the xenon lamp optical component 2 according to the configuration parameters.

[0027] Understandably, the simulation testing process includes: First, the spacecraft to be tested is placed inside vacuum container 1, the container is evacuated to a high vacuum state, and a cold black background simulation is initiated to reproduce the space thermal environment conditions. During the system design phase, simulation module 3, based on preset parameters such as irradiation area, working distance, and irradiation intensity, uses optical simulation software to establish a model of the xenon lamp optical component 2, and parametrically designs the surface shape of the condenser lens 23 to ensure that a single xenon lamp optical component 2 forms a uniform light spot on the target surface. Subsequently, a multi-lamp array model is established, with the irradiation uniformity of the tested surface as the optimization objective, iteratively calculating the optimal single-lamp spacing and array arrangement. After the initial optical design is completed, thermal simulation software is used to perform coupled analysis of the temperature field and flow field of the lamp array under vacuum and low-temperature conditions to verify the effectiveness of the forced air cooling solution and ensure that the xenon lamp electrode temperature is within a safe range. The configuration parameters determined by simulation optimization are stored in control module 4 as the operating reference parameters for control module 4. During test operation, control module 4 sends control commands to the drive power supply unit, which outputs a constant current drive current to each xenon lamp. The high-voltage trigger module sends a high-voltage pulse to ignite the xenon lamp, and then switches to constant current drive mode to maintain its stable arc discharge. The light radiation emitted by the xenon lamp is reflected and distributed by the condenser lens 23 inside the sealed protective container 21, and then projected onto the spacecraft test surface inside the vacuum container 1 through the quartz glass window of the light-emitting end face 213. Multiple xenon lamp optical components 2 work together in an optimized array arrangement, with weaker irradiation areas at the edges of adjacent lamps overlapping and compensating each other, thereby forming an external heat flow irradiation field with solar spectral characteristics and irradiation uniformity better than ±10% on the test surface. During lamp assembly operation, an external cooling gas source continuously supplies dry cooling gas into the sealed protective container 21 through the air inlet 211. The gas flows over the xenon lamp electrodes and the bulb (light-emitting area) 223, carrying heat as it is discharged from the air outlet 214, forming a forced convection cooling circuit. This effectively removes the large amount of heat generated by the xenon lamp during prolonged operation, ensuring stable and reliable lamp assembly operation in a vacuum environment. Simultaneously, the control module 4 collects real-time irradiance data from irradiance sensors positioned near the test surface and compares it with a preset target value. When irradiance drifts, the drive current is automatically adjusted for closed-loop compensation, maintaining stable external heat flow loading conditions on the test surface. Furthermore, the control module 4 can dynamically adjust the lamp array output power according to a preset orbital cycle operating condition curve, simulating changes in external heat flow during spacecraft operation in orbit. Ultimately, through irradiance loading by this system, the spacecraft completes a thermal balance test under simulated space vacuum thermal environment conditions.

[0028] In this implementation, the xenon lamp body 22 is isolated from the internal environment of the vacuum container 1 by the sealed protective container 21, so that the pressure atmosphere inside the container is maintained to allow for the convection of cooling gas. This solves the problems of xenon lamps being unable to be cooled by air and being prone to high-voltage breakdown in a vacuum environment, allowing the xenon lamp to operate directly inside the vacuum container 1. At the same time, the simulation module 3 determines the configuration parameters that meet the preset irradiance distribution requirements, and the control module 4 controls the operating status according to the configuration parameters. This balances the accuracy of solar spectrum simulation with the simplicity of system structure, providing realistic, controllable and reliable external heat flow simulation conditions for spacecraft thermal experiments.

[0029] like Figures 2 to 6 As shown, according to a specific embodiment of this application, the sealed protective container 21 has a cylindrical structure, the xenon lamp body 22 is arranged along the axial direction of the sealed protective container 21, and the optical axis of the xenon lamp body 22 is coaxially arranged with the axis of the sealed protective container 21; the xenon lamp optical assembly 2 also includes a bowl-shaped condenser lens 23, the bottom of the condenser lens 23 is provided with a bottom through hole 231, the xenon lamp body 22 passes through the bottom through hole 231, and the bowl opening of the condenser lens 23 faces the light-emitting end face 213 of the sealed protective container 21.

[0030] As is understandable, a xenon lamp is a gas discharge light source that uses the inert gas xenon as its working medium. Its light-emitting principle is as follows: after completely evacuating the bulb (light-emitting area) 223, a certain concentration of xenon gas is introduced. When a high-voltage pulse current is applied between the anode 221 and the cathode 222, exciting the cathode 222 to emit thermionic electrons, xenon atoms are excited and ionized, producing a strong arc light. Since the distance between the anode and cathode 221 is typically about 10 mm, it can be considered a point light source in engineering. Xenon lamps have extremely high irradiance, their spectral color is close to sunlight, and they have high brightness and good color rendering, making them one of the best color rendering light sources among current gas discharge lamps. Therefore, they are widely used in the experimental development of solar simulators.

[0031] Based on bulb structure, xenon lamps can be divided into two types: long-arc xenon lamps and short-arc xenon lamps. Considering luminous efficiency, a short-arc spherical xenon lamp body 22 is preferred. Its smaller arc spacing facilitates precise light distribution and energy focusing in the optical system, and is more suitable for the optical design requirements of external heat flow simulation. For example, a spherical short-arc xenon lamp with a rated power of 1600W is selected. The light beam is illuminated through the light-emitting end face 213, and filters can be added arbitrarily at the position of the light-emitting end face 213 to obtain the desired light wavelength. The bulb life generally exceeds 800 hours.

[0032] According to a specific embodiment of this application, the sealed protective container 21 has a cylindrical structure, and the xenon lamp body 22 is arranged along the axial direction of the sealed protective container 21. The optical axis of the xenon lamp body 22 is coaxial with the axis of the sealed protective container 21. The xenon lamp optical assembly 2 also includes a bowl-shaped condenser lens 23. The bottom of the condenser lens 23 has a bottom through hole 231, and the xenon lamp body 22 passes through the bottom through hole 231. The opening of the condenser lens 23 faces the light-emitting end face 213 of the sealed protective container 21. The light emitted by the xenon lamp body 22 is reflected by the reflective surface of the inner wall of the condenser lens 23 and emitted from the opening of the bowl in the form of a parallel or converging beam. It is then projected onto the test surface of the spacecraft to be tested outside the sealed protective container 21 through the light-emitting end face 213.

[0033] In this embodiment, by arranging the xenon lamp body 22 along the axial direction of the sealed protective container 21 and setting its optical axis coaxial with the axis of the container, and by inserting the bottom through hole 231 of the bowl-shaped condenser 23 through the xenon lamp body 22 with the bowl opening facing the light-emitting end face 213, the arc emitting area of ​​the xenon lamp is located at the focal position of the condenser 23, ensuring that the light radiation is efficiently focused and directionally emitted after being reflected by the condenser 23, thereby improving the light energy utilization rate; the coaxial layout makes the light field axially symmetrical, which is conducive to forming a uniform square light spot and meeting the strict requirements of irradiation uniformity for spacecraft thermal tests.

[0034] Furthermore, according to a specific embodiment of this application, the air inlet 211 is provided on the rear cover end face 215 of the sealed protective canister 21, and a cold air channel 212 is provided between the air inlet 211 and the through hole 231 at the bottom of the condenser lens 23. The cooling gas enters the bowl of the condenser lens 23 through the cold air channel 212, flows through the surface of the xenon lamp body 22 and is discharged from the air outlet 232 at the mouth of the bowl, and is discharged from the sealed protective canister 21 through the air outlet 214.

[0035] like Figure 5 As shown, when the xenon lamp body 22 and the condenser lens 23 are installed inside the sealed protective container 21, the bowl of the condenser lens 23 is adjacent to the inner wall of the sealed protective container 21. Although it is not completely sealed, the space between the two is limited. The gap between the two is not enough to exhaust the heat exchange gas flowing through the surface of the xenon lamp body 22 from the bowl space of the condenser lens 23. Therefore, an air outlet 232 is provided at the bowl of the condenser lens 23. Most of the heat exchange gas in the bowl space is discharged from the air outlet 232 to the bottom space of the bowl of the condenser lens 23, and then discharged from the sealed protective container 21 through the air outlet 214.

[0036] In this embodiment, by setting the air inlet 211 on the rear cover end face 215 of the sealed protective container 21, and setting a cold air channel 212 between the air inlet 211 and the through hole 231 at the bottom of the condenser lens 23, the cooling gas flows directionally into the bowl of the condenser lens 23, flows along the xenon lamp axis through its arc emitting area and electrode surface, and is discharged from the outlet 232 at the bowl opening, and finally discharged outside the container through the outlet 214, forming a forced convection cooling circuit from the bottom of the bowl to the bowl opening. This cooling circuit allows the cooling gas to flow precisely through the high-temperature area of ​​the xenon lamp, achieving directional and efficient heat dissipation of the xenon lamp; at the same time, the cooling gas is discharged from the bowl opening after completing heat exchange in the bowl space, avoiding the hot airflow from stagnating or flowing back in the container, ensuring that the xenon lamp operates stably for a long time in a vacuum environment, extending the lamp assembly life and ensuring the stability of light output. The structure of the bowl-shaped condenser lens 23 allows the bowl space to naturally form an airflow channel from the bottom of the bowl to the bowl opening, without the need for additional flow guiding structures, resulting in a compact overall structure and good assembly consistency.

[0037] Furthermore, according to a specific embodiment of this application, the configuration parameters include the surface shape parameters of the condenser lens 23, so that the light spot emitted by the condenser lens 23 is square on the test surface of the spacecraft under test.

[0038] Understandably, the surface parameters of the condenser lens 23 (including but not limited to surface curvature, aspheric coefficient, and local surface adjustment) determine the distribution of reflected light points on the target surface. When an axisymmetric reflector (such as a standard parabola or ellipsoid) is used, due to its rotational symmetry, the reflected light forms a circular spot on the target surface. When these circular spots are arrayed, there will inevitably be arc-shaped areas of weak irradiation between adjacent spots, making it impossible to achieve uniform coverage through simple overlap. This results in the overall irradiation uniformity failing to meet the accuracy requirements of spacecraft thermal testing.

[0039] In this embodiment, the surface parameters of the condenser lens 23 are adjusted through simulation optimization. For example, the axisymmetric constraint is broken by introducing differentiated curvatures or asymmetric higher-order terms in different meridional directions of the reflecting surface, causing the distribution of light rays on the target surface to change from circular to square. During the optimization process, the square spot shape and irradiance uniformity on the target surface are used as optimization objectives. The surface parameters of the condenser lens 23 (such as quadratic surface coefficients and higher-order aspherical coefficients) are set as adjustable variables. Iterative calculations are performed using the software's built-in optimization algorithm until the spot shape approaches a square and the uniformity converges to meet the requirements.

[0040] For the single-lamp emission module, a simulation model was built using Lighttools software to accurately simulate the light emission characteristics of the light source. Monte Carlo ray tracing was then used to obtain the light intensity distribution on the irradiation surface. Simulation results show that when using an axisymmetric reflector, the emitted light spot is circular, which is not conducive to obtaining uniform irradiation through subsequent multi-lamp splicing. Therefore, the reflector's surface shape was optimized to make the light spot projected onto the target surface square, facilitating array splicing. The optimized simulation results show that the overall shape of the light spot is square, but due to the obstruction of some light by the xenon lamp electrodes and the bulb (emission area) 223 support structure, a certain dark area exists in the central region of the light spot. This dark area is an inherent defect caused by the obstruction of the xenon lamp's own structure and is unrelated to the optimization results of the condenser lens 23's surface shape parameters. Surface shape optimization only changes the outer contour shape of the light spot from circular to square, without changing the distribution of the dark area caused by obstruction. This dark area can be compensated for by overlapping the light spot edges of adjacent lamps, or further homogenized through secondary light distribution and mixing superposition by subsequent reflectors, thereby obtaining a more uniform irradiation output.

[0041] Meanwhile, the formation of square light spots provides geometric adaptability for array splicing, making the edge overlap between adjacent light spots more regular and controllable, laying the foundation for subsequent overall uniformity optimization. Through the above methods, this application achieves the technical effect of forming a square uniform light spot on the target surface by a single xenon lamp optical component 2, effectively improving the irradiance uniformity when splicing multiple lamps.

[0042] Furthermore, according to a specific embodiment of this application, the condenser lens 23 adopts a non-intersecting optical path layout, and the edge of the condenser lens 23 does not block the light from the xenon lamp body 22.

[0043] Understandably, the condenser lens 23 has two design options: a converging light path and a parallel light path. The former uses a cross-beam path to avoid obstruction by the xenon lamp structure, resulting in a smaller reflector size, but light blocked by the xenon lamp structure at the rear end cannot be projected by the reflector. The latter uses a non-cross-beam path, where the entire xenon lamp blocks the light, and the reflector aperture becomes significantly larger. Preferably, a non-cross-beam path is used. For example, based on a simulation design with a working distance of 3m, a single lamp irradiance area of ​​0.8m × 0.8m, an aperture size of 300mm, and the irradiance surface implemented using a splicing method, the calculated exit angle of the edge rays is approximately 4.8°.

[0044] Furthermore, the reflective surface of the condenser lens 23 is coated with a silver protective film. This is intended to significantly increase the reflectivity of light and improve optical efficiency, while the protective film may also have anti-oxidation properties to maintain long-term stability of reflective performance.

[0045] Furthermore, the problem of central occlusion is improved by performing a special surface treatment on the condenser lens 23. Here, a textured or spark-like pattern is used to homogenize the light spot. For example, homogenization simulation is performed using 600-mesh, 220-mesh, and 120-mesh sand textures. According to the comparison, under the 120-mesh sand surface property, the irradiation uniformity is 7%, and the single-lamp irradiation energy is 1350W / m².

[0046] According to a specific embodiment of this application, the configuration parameters include array arrangement parameters of multiple xenon lamp optical components 2. The array arrangement parameters include at least the spacing between adjacent xenon lamp optical components 2, such that the edges of the light spots emitted by adjacent xenon lamp optical components 2 overlap with each other.

[0047] Furthermore, according to a specific embodiment of this application, the simulation module 3 iterates with the irradiation uniformity of the test surface as the target value and the spacing between adjacent xenon lamp optical components 2 as the variable to determine the array arrangement parameters.

[0048] Understandably, based on the optical model of a single xenon lamp, a multi-lamp array model is further established to design a uniform light field for the multi-xenon lamp array. First, an initial design of the array structure is performed, comprehensively considering the Gaussian distribution characteristics of the light intensity. Based on requirements such as irradiance area and working distance, combined with single-lamp power and lamp spacing, the overall layout is determined, selecting the optimal array size and arrangement. During the overall array design process, areas with weaker irradiance energy at the edges of adjacent lamps are overlapped, making the irradiance intensity in these areas close to the irradiance intensity at the center of a single lamp. This eliminates irradiance dips at the light spot junctions, ensuring the overall system meets the requirements for irradiance uniformity.

[0049] Based on this, with the irradiation uniformity of the test surface at a specified irradiation distance as the final optimization target, the spacing between adjacent xenon lamps was set as an adjustable variable. Through software simulation iteration, taking into account the feasibility of the structure, the final lamp array arrangement spacing was obtained.

[0050] For example, taking a 5×5 light array as an example, simulation results using 20 million ray tracing lines show that the total optical power received on the 2m×2m test surface is 8616.2W, the average illuminance is 2154.1W / m², corresponding to approximately 1.59 solar constants, and the irradiance non-uniformity is approximately 6.7%, which meets the requirements for irradiance uniformity in spacecraft thermal tests.

[0051] The optimization design of uniform light field of xenon lamp array is to set the irradiation uniformity of the measured surface at a specified irradiation distance as the final target value, and obtain the optimal single lamp spacing through software optimization iteration. The feasibility of the structure needs to be comprehensively considered.

[0052] Table 1. Comparison of Irradiance Performance under Different Xenon Lamp Powers According to a specific embodiment of this application, the simulation module 3 is used to simulate and determine the configuration parameters of the xenon lamp optical component 2 based on the optical parameters of the xenon lamp optical component 2, so that the light field emitted by the xenon lamp optical component 2 meets the preset irradiance distribution requirements.

[0053] First, an optical model is created using software. The modeling method is as follows: Based on technical specifications and usage requirements, the irradiance, irradiation area, and working distance of the lamp array system were initially determined. The required number of light sources and the power of a single lamp were calculated in conjunction with the system's energy utilization rate, and the xenon lamp specifications were further confirmed.

[0054] For xenon lamps with different selectable power, the light intensity distribution of the xenon lamp in the meridional plane and the arcuate plane at 360° was measured to obtain the light distribution curve, and a xenon lamp optical model was established based on this.

[0055] Based on the obtained xenon lamp light distribution curves and optical models, the condenser lens 23 and the single-lamp structure were designed. In the design of the single-lamp structure, the main consideration was that the light distribution intensity conformed to a Gaussian distribution. Based on the requirements of irradiation area and irradiation distance, the overall consideration was taken into account with the single-lamp power, lamp spacing and light distribution, and the optimal surface shape of the condenser lens 23 was selected.

[0056] Using LIGHTTOOLS software, the xenon lamp data and condenser lens 23 obtained above are modeled and simulated. The simulation model accurately simulates the shape and luminous characteristics of the light source. The Monte Carlo method is used to perform ray tracing to obtain the illuminance, intensity or brightness distribution on the irradiated surface, thus obtaining a three-dimensional simulation model of a single xenon lamp.

[0057] In a space environment simulation container environment, it is also necessary to consider the radiative heat transfer between the xenon lamp, test piece, tooling and space environment simulator, and to ensure that the xenon lamp meets the requirements for use in a vacuum environment through reasonable active and passive thermal control measures.

[0058] Thermal analysis and vacuum thermal environment adaptability of xenon lamp assembly: The electro-optical conversion efficiency of a xenon lamp is approximately 45%. Besides the conversion of electrical energy into light energy, the remainder is converted into heat energy, primarily concentrated at the lamp's electrodes, with a greater concentration at the anode (221). Prolonged exposure to high temperatures will affect the lamp's lifespan. Therefore, the impact of heat must be fully considered in the mechanical structure design of xenon lamps, requiring analysis of the heat dissipation and heat resistance of mechanical components.

[0059] Traditional solar simulators place the xenon lamps outside the vacuum container 1 and typically use air cooling or water cooling for heat dissipation. However, the solar lamp array of this application is placed entirely inside the vacuum container 1 and uses air cooling. An axial fan extracts the heat generated by the anode 221 from the concentrator mirror 23 through the heat dissipation holes, forming a directional airflow channel to achieve efficient heat dissipation and ensure that the xenon lamps can operate normally for a long time.

[0060] For the design of uniform light field of multi-xenon lamp array, a multi-lamp array model is established based on a single xenon lamp model, and the uniform light field of multi-xenon lamp array is designed.

[0061] First, an initial design of the lamp array structure is carried out, considering the Gaussian distribution characteristics of light intensity. Based on requirements such as irradiance area and irradiance distance, and taking into account individual lamp power and lamp spacing, the optimal number and layout of lamps are selected. Based on the individual lamp design results, and comprehensively considering performance indicators such as irradiance area, irradiance distance, irradiance uniformity, and irradiance energy, a multi-lamp array combination structure design is implemented. In the overall design of the lamp array, the key focus is on overlapping the areas with weaker irradiance energy at the edges of the lamps, making their irradiance intensity close to that of the center of each individual lamp. This eliminates irradiance dips at the joints, ensuring the overall system achieves uniformity.

[0062] The entire lamp array was simulated using LIGHTTOOLS optical simulation software to accurately simulate the optical characteristics of the light source. Monte Carlo ray tracing was then performed to obtain the illuminance distribution on the receiving surface. Based on the simulation results, the optimal multi-lamp array arrangement was determined for the required working distance.

[0063] The design of uniform light field optimization for multi-xenon lamp arrays refers to setting the irradiation uniformity of the test surface as the optimization target value under a specified irradiation distance, using the spacing between individual lamps as a variable for simulation, and then iteratively optimizing through software, taking into account the feasibility of the structure, to obtain the optimal spacing between individual lamps.

[0064] In summary, this study investigates the design of a uniform light field for a multi-xenon lamp array by employing a research approach that includes single-lamp modeling, optical design, simulation modeling, and optimization design. Through repeated software optimization and iteration, and by comprehensively considering factors such as single-lamp structure, irradiation energy, irradiation uniformity, irradiation distance, and single-lamp spacing, the optimal multi-xenon lamp array structure design is finally obtained.

[0065] According to a specific implementation of this application, the control module 4 also stores a preset orbital period external heat flow change curve. The control module 4 controls the output irradiance of the xenon lamp optical component 2 according to the change curve to simulate the time-varying characteristics of external heat flow during the spacecraft's on-orbit operation.

[0066] Understandably, when a spacecraft is in orbit, the external heat flux received on its surface varies periodically with factors such as orbital position and solar incidence angle. To reproduce this dynamic thermal environment in ground-based thermal experiments, control module 4 has a pre-defined external heat flux variation curve for the orbital period. This curve, pre-generated based on the spacecraft's orbital parameters, attitude, and mission profile, describes the time-varying pattern of the spacecraft's surface heat flux density within one orbital period, typically including high heat flux in the illuminated area, low heat flux in the shadow area, and the transition segment when entering and exiting the shadow.

[0067] During the experiment, control module 4, following a preset timing curve, adjusted the output current of the xenon lamp drive power supply to control the irradiance of the xenon lamp optical component 2 on the test surface in real time, making it follow the curve's changes, thereby simulating the dynamic changes in the spacecraft's extraorbital heat flux. This control mode is a programmable open-loop regulation, with a time scale consistent with the orbital period, used to simulate the alternating changes in heat flux between the illuminated and shadowed areas of the spacecraft.

[0068] In this embodiment, not only can steady-state solar simulated irradiation be provided, but the irradiation output can also be dynamically adjusted according to a preset orbital period, making the external heat flow loading conditions of the ground thermal test closer to the real on-orbit thermal environment, and providing more accurate test data for the verification of the spacecraft thermal control system.

[0069] According to a specific embodiment of this application, the system further includes a high-voltage triggering module and a constant current drive power supply; The high-voltage trigger module is installed at the rear cover flange of the sealed protective canister 21 and is electrically connected to the xenon lamp body 22 through a high-voltage wire passing through the rear cover flange. The high-voltage trigger module is used to apply a high-voltage pulse to the xenon lamp body 22 to ignite the xenon lamp body 22. The constant current drive power supply is electrically connected to the xenon lamp body 22 and is used to output a constant current to the xenon lamp body 22 after the xenon lamp body 22 is ignited.

[0070] Among them, the output current is adjusted in real time to maintain the stable arc discharge of the xenon lamp body 22.

[0071] Understandably, the xenon lamp body 22 is a gas discharge light source, and its startup requires a high breakdown voltage. At normal temperature and pressure, the breakdown voltage of xenon gas is typically in the tens of thousands of volts range; in low temperature and low pressure environments, the ignition voltage may increase further. Therefore, a high-voltage trigger module is provided to apply an instantaneous high-voltage pulse to the xenon lamp body 22 during startup, ionizing the xenon gas and establishing an initial arc channel, thereby igniting the xenon lamp body 22.

[0072] After ignition, the xenon lamp enters the arc discharge stage. A constant current drive power supply is set. After the xenon lamp body 22 is ignited, it switches to constant current drive mode. The output current is sampled in real time through closed-loop control and compared and adjusted with the preset value to maintain a constant output current, overcome the influence of lamp parameter changes, and ensure long-term stable arc discharge of the xenon lamp.

[0073] Meanwhile, the high-voltage trigger module is installed at the rear cover flange of the sealed protective canister 21, and is electrically connected to the xenon lamp body 22 inside the canister via a high-voltage wire passing through the rear cover flange. This installation method minimizes the high-voltage transmission path between the high-voltage trigger module and the xenon lamp body 22 inside the canister, reducing energy loss and waveform distortion of the high-voltage pulse during transmission, and improving the reliability of triggering and the success rate of ignition. When the high-voltage wire passes through the rear cover flange, it is fixed and sealed by a sealed insulation structure, ensuring both electrical insulation between the high-voltage wire and the flange, and airtightness of the sealed protective canister 21 at the wire-passing location. The trigger module is located outside the canister, and in case of failure, it can be directly disassembled and replaced externally without opening the sealed protective canister 21, reducing maintenance difficulty. The high-voltage trigger module and the constant current drive power supply work together, with the high-voltage trigger module first completing the startup, and then switching to the constant current drive power supply to maintain stable operation. The two work together to complete the entire process control of the xenon lamp from startup to stable operation.

[0074] For example, a xenon lamp driver power supply with a rated power of 2kW. Its core operating point is an output current of 70A and a lamp voltage of 28V, providing an actual driving power of 1960W. By adjusting the current knob on the power supply panel, the user can directly set and precisely control the current value of the xenon lamp. Based on the constant current driving principle, this operation can linearly and precisely adjust the output power of the xenon lamp, thereby achieving stable control of its output light intensity and ensuring the illumination stability of the entire optical system.

[0075] According to a specific embodiment of this application, the system also includes an irradiance sensor, which is set at the test surface of the spacecraft under test or at the light-emitting surface of the xenon lamp optical component 2, for collecting actual irradiance data and feeding it back to the control module 4; the control module 4 adjusts the driving current of the xenon lamp body 22 according to the comparison result between the actual irradiance data and the target irradiance value.

[0076] It is understandable that during spacecraft thermal testing, the output irradiance of the xenon lamp optical component 2 may drift due to factors such as xenon lamp aging, cooling gas temperature fluctuations, or power supply voltage changes. To ensure long-term stability of the irradiance on the test surface, this application installs an irradiance sensor at the test surface or the light-emitting surface to collect actual irradiance data in real time and feed it back to the control module 4. The control module 4 compares the actual irradiance with the preset target value and automatically adjusts the xenon lamp drive current according to the deviation, realizing closed-loop feedback control to compensate for irradiance drift and ensure the accuracy and repeatability of test conditions. The specific installation location of the irradiance sensor can be flexibly selected according to test requirements and site conditions.

[0077] According to a specific embodiment of this application, the sealed protective container 21 is provided with a window flange and a rear cover flange at both ends. A quartz glass window is fixed at the window flange, allowing light emitted from the xenon lamp body 22 to exit to the outside of the sealed protective container 21 and be transmitted to the test surface of the spacecraft under test. The window flange adopts a thickened structural design to enhance its rigidity and resistance to deformation, ensuring that the optical alignment accuracy and sealing integrity of the window are not affected when subjected to vacuum pressure difference and thermal stress. The rear cover flange is used to install the high-voltage trigger module and the power input interface, and forms a reliable seal with the rear end of the container.

[0078] The sealed protective container 21 is made of stainless steel using a one-piece molding process. It has high strength, excellent pressure resistance, and dimensional stability in a vacuum environment. It can effectively resist the pressure difference between the inside and outside of the vacuum container 1, ensuring the structural safety of the container under vacuum or low-pressure conditions. The surface of the container is appropriately treated to meet the vacuum release rate requirements, avoiding contamination of the internal environment of the vacuum container 1.

[0079] The sealed protective canister 21 is equipped with two airtight interfaces, located at its rear. One interface serves as an inlet pipe, connecting to an external cooling gas source to introduce cooling gas into the canister. The other interface serves as an exhaust pipe, expelling the gas carrying heat after flowing through the xenon lamp body 22 and the condenser lens 23, thus forming a complete forced air-cooling circulation loop together with the inlet pipe interface. The airtight interfaces preferably adopt the KF40 standard interface form, achieving a vacuum-level sealed connection with the external pipeline via a metal sealing ring. Positioning both airtight interfaces at the rear of the canister 21 facilitates the centralized arrangement of the inlet and outlet pipes at the rear of the canister, preventing obstruction or interference of the light path from the front quartz glass window. It also facilitates the unified binding and routing management of the pipes inside the vacuum container 1.

[0080] The air-cooling system includes a cold air inlet located at the bottom of the condenser lens 23 and an air outlet 214 located at the bowl-shaped opening of the condenser lens 23. The cold air inlet is located in the central area at the bottom of the condenser lens 23 and is connected to the air intake pipe interface at the rear of the sealed protective canister 21, used to guide external cooling airflow to the high-temperature area adjacent to the xenon lamp anode 221. The air outlet 214 is located at the edge of the bowl-shaped opening of the condenser lens 23 and is connected to the exhaust pipe interface at the rear of the sealed protective canister 21, used to exhaust the hot airflow that has flowed through the xenon lamp surface and the inner cavity of the condenser lens 23 outside the canister. A cooling air duct is formed between the cold air inlet and the air outlet 214 through the bowl-shaped space between the condenser lens 23 and the xenon lamp. After entering through the cold air inlet, the cooling gas flows directionally along the air duct through the surfaces of the xenon lamp anode 221, cathode 222, and bulb (light-emitting area) 223. After fully absorbing the heat generated by each component, it is discharged from the air outlet 214, thereby establishing a forced convection circulation inside the condenser lens 23. This achieves efficient and uniform cooling of the xenon lamp and condenser lens 23, ensuring that the temperature rise of the lamp assembly is controllable and the light output is stable during continuous operation.

[0081] All flange connections and interfaces are leak-tested using helium mass spectrometry to ensure that the vacuum leakage rate after assembly is better than the preset requirements, thereby ensuring that the xenon lamp can operate reliably for a long time inside the vacuum container 1.

[0082] The electro-optical conversion efficiency of a xenon lamp is approximately 45%. Therefore, besides the conversion of electrical energy into light energy, the remainder is converted into heat energy, primarily concentrated at the two electrodes of the xenon lamp, with the anode (221) generating the most heat. Prolonged exposure to high temperatures will affect the lifespan of the xenon lamp. Therefore, the impact of heat must be fully considered in the mechanical structure design of xenon lamps, and the heat dissipation and heat resistance of mechanical components must be analyzed.

[0083] This application uses COMSOL Multiphysics multiphysics coupling simulation to systematically analyze the thermal performance of xenon lamps under actual operating conditions, focusing on the temperature field distribution of the condenser lens 23 and the xenon lamp assembly under steady-state operating conditions. The thermal simulation boundary conditions are set as follows: ambient temperature 20℃, initial temperature 20℃, surface-to-environment heat transfer coefficient 10 W / (m²·K), air velocity at inlet 211 12 m / s, and diameters of both inlet 211 and outlet 214 40 mm.

[0084] Simulation results show that the highest temperature of the lamp is located at the lamp tube, which is about 160℃; the lowest temperature at the lamp housing is about 20℃. When the air velocity at the air inlet 211 is 12 m / s, the air velocity at the air outlet 214 is about 17 m / s, the flow velocity around the xenon bulb housing (light-emitting area) 223 is mostly between 8 and 10 m / s, and the pressure inside the reflective surface is mostly around 450 Pa.

[0085] Based on thermal simulation analysis and performance targets, the cooling system design meets the following requirements: the air inlet 211 can stably provide an inlet air velocity of not less than 12 m / s; the rated pressure of the air inlet 211 is greater than 1000 Pa; and the inlet air temperature is approximately 20℃.

[0086] Simulation results verify the rationality of the current mechanical structure and heat dissipation design, which can meet the requirements of the actual operating environment and ensure that the xenon lamp can work stably for a long time in a vacuum environment.

[0087] The flowcharts and block diagrams in the accompanying drawings illustrate the architecture, functionality, and operation of possible implementations of systems, methods, and computer program products according to various embodiments of this application. In this regard, each block in a flowchart or block diagram may represent a module, segment, or portion of code containing one or more executable instructions for implementing a specified logical function. It should also be noted that in some alternative implementations, the functions indicated in the blocks may occur in a different order than those indicated in the drawings. For example, two consecutively indicated blocks may actually be executed substantially in parallel, and they may sometimes be executed in reverse order, depending on the functions involved. It should also be noted that each block in the block diagrams and / or flowcharts, and combinations of blocks in the block diagrams and / or flowcharts, can be implemented using a dedicated hardware-based system that performs the specified function or operation, or using a combination of dedicated hardware and computer instructions.

[0088] The units described in the embodiments of this application can be implemented in software or hardware. The names of the units are not, in some cases, limiting the scope of the unit itself.

Claims

1. A vacuum thermal environment simulation test system for spacecraft, characterized in that, The system includes: A vacuum container used to house a spacecraft to be tested; At least one xenon lamp optical assembly is disposed inside the vacuum container for outputting simulated solar irradiation to the spacecraft under test; the xenon lamp optical assembly includes a sealed protective canister and a xenon lamp body disposed inside the sealed protective canister, wherein the sealed protective canister is provided with an air inlet and an air outlet, the air inlet is used to introduce cooling gas into the sealed protective canister, and the air outlet is used to discharge the cooling gas flowing over the surface of the xenon lamp body from the sealed protective canister; The simulation module is used to simulate and determine the configuration parameters of the xenon lamp optical component based on the optical parameters of the xenon lamp optical component, the configuration parameters being such that the light field emitted by the xenon lamp optical component meets the preset irradiance distribution requirements; A control module, connected to the xenon lamp optical component and the simulation module, is used to control the operating state of the xenon lamp optical component according to the configuration parameters.

2. The system according to claim 1, characterized in that, The sealed protective canister has a cylindrical structure, the xenon lamp body is arranged along the axial direction of the sealed protective canister, and the optical axis of the xenon lamp body is coaxial with the axis of the sealed protective canister. The xenon lamp optical assembly also includes a bowl-shaped condenser lens. The bottom of the condenser lens has a bottom through hole, and the xenon lamp body passes through the bottom through hole. The opening of the condenser lens faces the light-emitting end face of the sealed protective canister.

3. The system according to claim 2, characterized in that, The air inlet is located on the rear cover end face of the sealed protective canister. A cold air channel is provided between the air inlet and the through hole at the bottom of the condenser lens. Cooling gas enters the bowl of the condenser lens through the cold air channel, flows over the surface of the xenon lamp body, and is discharged from the air outlet at the bowl opening, and then discharged from the sealed protective canister through the air outlet.

4. The system according to claim 2, characterized in that, The configuration parameters include the surface shape parameters of the condenser lens, so that the light spot emitted by the condenser lens is square on the test surface of the spacecraft under test.

5. The system according to claim 2, characterized in that, The condenser lens adopts a non-intersecting optical path layout, and the rim of the condenser lens does not block the light from the xenon lamp body.

6. The system according to claim 1, characterized in that, The configuration parameters include array arrangement parameters of the multiple xenon lamp optical components, and the array arrangement parameters include at least the spacing between adjacent xenon lamp optical components, the spacing being such that the edges of the light spots emitted by adjacent xenon lamp optical components overlap.

7. The system according to claim 6, characterized in that, The simulation module iterates using the irradiation uniformity of the test surface of the spacecraft under test as the target value and the spacing between adjacent xenon lamp optical components as the variable to determine the array arrangement parameters.

8. The system according to claim 1, characterized in that, The control module also stores a preset orbital period external heat flow variation curve. The control module controls the output irradiance of the xenon lamp optical component according to the variation curve to simulate the time-varying characteristics of external heat flow during the spacecraft's on-orbit operation.

9. The system according to claim 1, characterized in that, The system also includes a high-voltage triggering module and a constant current drive power supply; The high-voltage triggering module is installed at the rear cover flange inside the sealed protective canister and is electrically connected to the xenon lamp body through a high-voltage wire passing through the rear cover flange. The high-voltage triggering module is used to apply a high-voltage pulse to the xenon lamp body to ignite the xenon lamp body. The constant current drive power supply is electrically connected to the xenon lamp body and is used to output a constant current to the xenon lamp body after the xenon lamp body is ignited.

10. The system according to claim 1, characterized in that, The system also includes an irradiance sensor, which is installed on the test surface of the spacecraft under test or on the light-emitting surface of the xenon lamp optical assembly, for collecting actual irradiance data and feeding it back to the control module; The control module adjusts the driving current of the xenon lamp body based on the comparison between the actual irradiance data and the target irradiance value.

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