Satellite low-brightness design and analysis method based on satellite thermal control model

Abstract

The invention discloses a satellite low-brightness design and analysis method based on a satellite thermal control model, and belongs to the technical field of satellites. The method comprises the steps of task analysis, star catalogue thermal control low-brightness design, satellite thermal control-brightness analysis integrated modeling, thermal control feasibility analysis, satellite brightness analysis based on a thermal control model, index satisfaction degree analysis and the like. At present, a theoretical calculation method of a simplified model is generally used for brightness analysis of a satellite, and can not be effectively iterated and updated in time according to a thermal control star catalogue design condition of the satellite. According to the design and analysis method, the thermal control design and the brightness design and analysis of the satellite are integrated, and the low-brightness design is realized while the thermal control design is performed; and establishing an analysis model with unified thermal control and brightness analysis, and carrying out statistical analysis of the satellite brightness based on thermal analysis model data. According to the method, the satellite low-brightness design and the thermal design are organically combined, and the efficiency and the accuracy of the brightness design are improved.

Description

TECHNICAL FIELD

[0001] The present application relates to a satellite low-brightness design and analysis method based on a satellite thermal control model, in particular, a satellite thermal control model is reused to carry out satellite brightness design, analysis and calculation, and quantitative, accurate and efficient satellite brightness design is realized. BACKGROUND

[0002] Traditional satellite star table design does not consider the low-brightness factor, and a large amount of sunlight will be reflected, and the brightness is very high; with the deployment of large-scale low-orbit constellation represented by the star chain, the number of satellites in low earth orbit is increasing, and a large number of high-brightness satellites have a great impact on scientific activities such as ground astronomical observation and space astronomical observation, so it is necessary to carry out satellite low-brightness design.

[0003] However, there is currently a lack of quantitative and rapid satellite brightness design and analysis method, especially considering the complex geometric structure and surface characteristics of the satellite surface, it is difficult to effectively evaluate the brightness of the satellite. The traditional method can only be equivalent to a two-dimensional plane, a sphere, a cube and other simple geometric shapes, and the brightness is roughly evaluated, and the accuracy of the analysis result of this method is insufficient.

[0004] On the other hand, a thermal control model is established in detail in the process of satellite thermal analysis and thermal design, which actually includes the complex geometric shape of the satellite surface, the thermal-optical characteristics of each device and surface; in the past research, the model is only used for satellite temperature analysis and calculation, and in fact, it can play a role in the optical aspect, especially in the brightness analysis aspect. SUMMARY

[0005] The technical problem solved by the present application is to overcome the shortcomings of the prior art and provide a satellite low-brightness design and analysis method based on a satellite thermal control model, which solves the problem of satellite brightness design and analysis.

[0006] The technical solution of the present application is: a satellite low-brightness design and analysis method based on a satellite thermal control model, comprising:

[0007] According to the thermal control requirements and low-brightness requirements of the satellite, the factors affecting the temperature and brightness of the satellite are analyzed, the thermal design working condition and the brightness design working condition are determined, the temperature-brightness integrated design working condition is formed by combining the two, and the working condition parameters in the temperature-brightness integrated design working condition are determined, the satellite external heat flow analysis and illumination condition analysis are carried out, and the external heat flow level and illumination level of each surface of the satellite are calculated;

[0008] According to the temperature-brightness integrated design working condition, the working condition parameters, the external heat flow level and the illumination level, the satellite surface thermal control low-brightness design is carried out;

[0009] According to the result of the satellite surface thermal control low-brightness design, a satellite thermal control model is established;

[0010] According to the temperature-brightness integrated design working condition and the satellite thermal control model, satellite thermal control feasibility analysis and satellite brightness analysis are sequentially carried out, and the analysis results are compared with the thermal control requirements and low-brightness requirements of the satellite to confirm whether the indexes are met; when the indexes are not met, the satellite surface thermal control low-brightness design is re-performed until the requirements are met.

[0011] Further, the satellite surface thermal control low-brightness design comprises:

[0012] On the basis of the external heat flow analysis, the heat dissipation surface of the satellite surface is distributed, comprising:

[0013] For the structural plate of the carbon fiber skin, the skin is used as the low-brightness heat dissipation surface;

[0014] For the structural plate of the aluminum skin, black paint is sprayed or black film is pasted at the position of the heat dissipation surface to realize the low-brightness design of the heat dissipation surface;

[0015] For the satellite surface of the non-heat dissipation surface, multi-layer surface film is wrapped, and a double-layer perforated black surface film is installed in a staggered manner;

[0016] For other positions and devices of the satellite surface, a thermal control black paint coating, a pasted black surface film or a wrapped multi-layer black surface film is used for low-brightness design, and when the multi-layer black surface film is used, a double-layer perforated black surface film is installed in a staggered manner.

[0017] Further, the multi-layer surface film is selected from black polyimide film, and the solar absorption ratio of the film surface is 0.78 or above.

[0018] Further, the establishment of the satellite thermal control model comprises: according to the satellite surface thermal control low-brightness design, a thermal analysis model of the satellite is established; wherein when the thermal optical properties of the surface modeling heat dissipation surface, multi-layer and device surface are determined, parameters including solar absorption ratio and solar reflectivity, refractive index are determined, which are used for subsequent brightness analysis; the appearance of the thermal analysis model is set, the low-brightness surface model grid is set to black, and the high-brightness surface is set to white or other colors, so as to synchronously evaluate the satellite brightness during the modeling process, and the high-brightness surface is modified and designed in time.

[0019] Further, the thermal control feasibility analysis comprises:

[0020] The thermal analysis model is used to perform satellite thermal analysis calculation based on the temperature-brightness integrated design condition, to analyze the temperature of each device on the satellite, to judge whether the temperature meets the index requirement, to modify the satellite heat dissipation surface and the multilayer surface film when the temperature does not meet the requirement, to evaluate the weight and power consumption of the satellite thermal control sub-system when the temperature meets the index requirement, and to indicate that the design is feasible after the weight and power consumption meet the technical requirement.

[0021] Further, the satellite brightness analysis comprises:

[0022] In the thermal analysis model, the sensing surface at different positions is established, the satellite albedo energy obtained on the sensing surface is obtained through space external heat flow calculation based on Monte Carlo and ray tracing algorithm, and the satellite brightness is calculated equivalently.

[0023] Further, the sensing surface is provided with material properties with a solar absorption ratio of 1, the distance between the sensing surface and the satellite thermal control model should be more than 10 times of the satellite scale, the area of the sensing surface should be within 20% of the cross-sectional area of the satellite, and the position of the sensing surface should avoid the solar-satellite connecting line to avoid shielding the effective external heat flow of the satellite.

[0024] A computer readable storage medium stores a computer program, and the computer program is executed by a processor to implement the steps of the satellite low brightness design and analysis method based on a satellite thermal control model.

[0025] A satellite low brightness design and analysis device based on a satellite thermal control model comprises a memory, a processor, and a computer program stored in the memory and executable on the processor, and the processor executes the computer program to implement the steps of the satellite low brightness design and analysis method based on a satellite thermal control model.

[0026] Compared with the prior art, the present application has the following advantages:

[0027] (1) The brightness design and analysis are based on the thermal analysis model of the satellite, and the satellite optical analysis model does not need to be re-established, which greatly improves the work efficiency;

[0028] (2) The three-dimensional thermal control model is used to calculate the satellite brightness, and compared with the existing two-dimensional plane equivalent calculation method, the calculation accuracy is higher, and more complex satellite orbit and attitude conditions can be considered;

[0029] (3) Most of the calculation work in the model-based satellite brightness calculation process is automatically completed by the computer and the software, and a large amount of data setting and calculation is not needed manually, which is more efficient and facilitates the iteration of the design process;

[0030] (4) The thermal control model and the brightness analysis model are integrated, which can effectively fuse the two factors and avoid the adverse effects of brightness design on satellite thermal control design. BRIEF DESCRIPTION OF DRAWINGS

[0031] Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The detailed description is made with reference to the accompanying drawings.

[0032] Figure 1 The figure is a schematic diagram of the method of the present application. DETAILED DESCRIPTION

[0033] In order to better understand the above technical solutions, the technical solutions of the present application will be described in detail below by means of the accompanying drawings and specific embodiments. It should be understood that the embodiments of the present application and the specific features in the embodiments are detailed descriptions of the technical solutions of the present application, and are not limitations of the technical solutions of the present application. In the case of no conflict, the technical features in the embodiments of the present application and the embodiments can be combined with each other.

[0034] Satellite low-brightness design is to reduce the visible brightness of satellite in space by technical means, and reduce the light pollution interference to ground astronomical observation.

[0035] The satellite low-brightness design and analysis method based on satellite thermal control model provided by the embodiments of the present application will be described in further detail below in combination with the accompanying drawings of the specification, such as Figure 1 The specific implementation mode can include:

[0036] According to the thermal control requirements and low-brightness requirements of the satellite, the factors affecting the temperature and brightness of the satellite are analyzed, the thermal design working condition and the brightness design working condition are determined, the two are combined to form a temperature-brightness integrated design working condition, and the working condition parameters in the temperature-brightness integrated design working condition are determined, the satellite external heat flow analysis and illumination condition analysis are carried out, and the external heat flow level and illumination level of each surface of the satellite are calculated;

[0037] According to the temperature-brightness integrated design working condition and its working condition parameters and external heat flow level and illumination level, the satellite surface thermal control low-brightness design is carried out.

[0038] According to the results of the satellite surface thermal control low-brightness design, a satellite thermal control model is established.

[0039] Based on the temperature-brightness integrated design working condition and the satellite thermal control model, satellite thermal control feasibility analysis and satellite brightness analysis are carried out in turn, and the analysis results are compared with the thermal control requirements and low brightness requirements of the satellite to confirm whether the indicators are met; when the indicators are not met, the satellite surface thermal control low brightness design is re-performed until the requirements are met.

[0040] In the technical scheme provided in the embodiments of the present application, the following steps are specifically included:

[0041] 1) task analysis

[0042] 11) The thermal control requirements and low brightness requirements of the satellite are analyzed, the indicators are determined, the factors affecting the temperature and brightness of the satellite are analyzed, the thermal design working condition and the brightness design working condition are determined, and the two are combined to form the temperature-brightness integrated design working condition;

[0043] 12) Through the task analysis of 11), the satellite orbit, attitude and other parameters in the working condition are determined, especially the illumination conditions for satellite brightness calculation are determined through the parameters of sun angle, earth angle, etc.

[0044] 13) According to the working condition parameters determined in 12), satellite external heat flow analysis and illumination condition analysis are carried out, the external heat flow level and illumination level of each surface of the satellite are calculated, and input is provided for heat dissipation surface design and low brightness design.

[0045] 2) Star table thermal control low brightness design

[0046] 21) According to the task analysis and established design working condition in 1), on the basis of external heat flow analysis, the heat dissipation surface of the satellite surface is distributed, for the carbon fiber skin structure plate, the skin is directly used as the low brightness heat dissipation surface; for the aluminum skin structure plate, black paint is sprayed or black film is pasted at the position of the heat dissipation surface to realize the low brightness design of the heat dissipation surface;

[0047] 22) For the satellite surface of non-heat dissipation surface, multi-layer coating is adopted, the multi-layer film is selected to be black polyimide carburizing film or other kinds of black film, and the surface film absorption ratio should be above 0.78, in order to balance the low brightness and air permeability requirements, the implementation is carried out in the way of double-layer perforated black film staggered hole installation;

[0048] 23) For other positions and devices of the satellite surface, such as antenna, mechanism surface, etc., it is required to use thermal control black paint coating, paste black film or implement low brightness design in the way of multi-layer black film coating, and when the multi-layer black film is used, the implementation is carried out in the way of double-layer perforated black film staggered hole installation;

[0049] 3) Satellite thermal control-brightness analysis integrated modeling

[0050] 31) According to the satellite thermal control design in 2), a thermal analysis model of the satellite is established, and the thermal optical properties of the heat dissipation surface, multilayer, and device surface in the satellite modeling need to be clear about the parameters such as solar absorption ratio and solar reflectivity, refractive index, etc., which are used for subsequent brightness analysis;

[0051] 32) During the modeling process, the appearance of the model is set, the low-brightness surface model grid is set to black, and the high-brightness surface is set to white or other colors, so as to synchronously evaluate the satellite brightness during the modeling process, and the high-brightness surface is modified in time.

[0052] 4) Thermal control feasibility analysis

[0053] 41) Using the satellite thermal analysis model established in 3), based on the analysis conditions established in 1), the satellite thermal analysis calculation is carried out, the temperature of each device on the satellite is analyzed, and it is judged whether it meets the index requirement, when it does not meet the requirement, the satellite heat dissipation surface, multilayer, etc. need to be modified;

[0054] 42) After the temperature of the device on the satellite meets the requirement, the weight and power consumption of the satellite thermal control subsystem are evaluated, and after it is determined that it meets the technical requirements, it is shown that the design is feasible.

[0055] 5) Satellite brightness analysis based on thermal control model

[0056] Reuse 3) to establish the satellite thermal control model for brightness analysis, based on the angular coefficient, external heat flow, and space irradiation calculation method used in the satellite thermal analysis process, establish the perception surface at different positions in the model, set the material properties of the perception surface to the solar absorption ratio of 1, the distance between the perception surface and the satellite body model should be more than 10 times the satellite scale, the area of the perception surface is equivalent to the cross-sectional area of the satellite, and its position should avoid the solar-satellite line to avoid shielding the effective external heat flow of the satellite; through the space external heat flow calculation based on the Monte Carlo and ray tracing algorithm, the satellite albedo energy obtained on the perception surface is obtained, and the satellite brightness is further calculated. The method considers the complex geometric conditions of the satellite surface, and has higher calculation accuracy.

[0057] 5) Index satisfaction confirmation

[0058] According to the task analysis 1), compare the technical requirements of the satellite overall thermal control design and brightness design with the satellite thermal calculation results obtained in 4) and the brightness calculation results obtained in 5), confirm whether the index is met, when the index is not met, adjust the satellite thermal control and brightness design again, iterate the above steps until the requirement is met.

[0059] Taking a communication satellite as an example, assuming that a low-orbit communication satellite is designed and analyzed, the configuration is a simple hexahedron, the orbit is a sun-synchronous circular orbit with an altitude of 500 km and a descending node local time of 10:00 AM, the satellite attitude keeps +Z to the ground and +X along the flight direction; the requirement is that the brightness of the ground observation satellite is darker than alpha star, the design is carried out and the satisfaction is analyzed.

[0060] The implementation steps of the present application are as follows:

[0061] 1. The task analysis steps are as follows:

[0062] a) Analyze the overall scheme, configuration layout, working mode, orbit, attitude and other constraints of the satellite, and clearly define the overall temperature control requirements of the on-board equipment and the low brightness requirements of the satellite; according to the above analysis, the design working conditions combined with thermal analysis and brightness analysis are designed;

[0063] b) For the design working conditions, the software with orbit thermal analysis function (such as SystemaThermica, ThermalDesktop) is used to analyze the satellite's arriving external heat flow data.

[0064] 2. The low brightness design steps of the star table are as follows:

[0065] a) According to the calculation results of the external heat flow in the task analysis, the positions and types of the satellite heat dissipation surfaces are selected; for this example, the surfaces of the satellite can be designed with different sizes and effects of heat dissipation surfaces, since the target of brightness analysis is the ground observation brightness, the -Z surface to the sky will not affect the brightness, so the -Z surface heat dissipation surface of the satellite can use white paint heat dissipation surface, and the other surface heat dissipation surface uses black paint heat dissipation surface;

[0066] b) After the heat dissipation surface is determined, the remaining position of the satellite cabin plate is covered with multiple layers, and all the multi-layer surface films use double-layer black surface film; the protruding antennas, solar wing supports and the like of the star table also use black paint or black surface film multi-layer to reduce the brightness.

[0067] 3. Integrated modeling of satellite thermal control and brightness analysis

[0068] a) The thermal analysis software (such as ThermalDesktop) is used to establish the thermal analysis model of the satellite according to the satellite thermal control design, configuration layout, working mode and equipment matching, etc., and the thermal optical properties of the surfaces of the star table modeling, such as heat dissipation surface, multi-layer, equipment, etc., need to be clear about the parameters of solar absorption ratio and solar reflectivity, refractive index, etc., which are used for subsequent brightness analysis;

[0069] b) During the modeling process, the appearance of the model is set, the low brightness surface model grid is set to black, and the high brightness surface is set to white or other colors, and the satellite brightness is evaluated synchronously during the modeling process, and for the high brightness surface, especially to the ground, the type of coating is changed.

[0070] 4. Thermal control feasibility analysis

[0071] a) Using thermal analysis software, satellite thermal simulation analysis is carried out according to the design working condition, the maximum temperature and the minimum temperature of the on-board equipment under each working condition are obtained, and it is judged whether it is within the technical requirement range or not;

[0072] b) The thermal design result is counted, the thermal control design weight is analyzed, the thermal analysis result is counted, the thermal control power consumption is analyzed, the technical requirements of the overall thermal control are compared, and it is judged whether the thermal control design is feasible or not.

[0073] 5. Satellite brightness analysis based on thermal control model

[0074] In the thermal analysis model of the satellite, a brightness sensor (sensing surface) is established, and the distance and size of the sensor and the satellite are reasonably designed according to the observation position requirement, the satellite size and the like; after the modeling is completed, the thermal simulation analysis working condition is modified, and the external heat flow calculation (temperature field calculation is not necessary) is carried out; the analysis calculation result is counted, the satellite reflected solar heat flux density reaching the sensor position is counted, and further conversion is carried out to obtain the brightness calculation results β1, β2, β3 and the like under different working conditions.

[0075] 6. Index satisfaction confirmation

[0076] The satellite brightness β1, β2, β3 calculated in the last step is compared with the brightness index α, it is judged whether the satellite satisfies the index under each working condition or not, and the satellite brightness design and analysis based on the satellite thermal control model are completed.

[0077] The application provides a computer readable storage medium, the computer readable storage medium stores computer instructions, when the computer instructions run on the computer, make the computer execute Figure 1 The method.

[0078] Those skilled in the art should understand that the embodiments of the application can be provided as a method, a system or a computer program product. Therefore, the application can adopt a complete hardware embodiment, a complete software embodiment or an embodiment combining software and hardware aspects. Moreover, the application can adopt the form of a computer program product implemented on one or more computer usable storage media (including but not limited to magnetic disk storage and optical storage) containing computer usable program code.

[0079] The computer program instructions can also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer-implemented process such that the instructions which execute on the computer or other programmable apparatus provide steps for implementing the functions specified in the flowchart block or blocks. Figure 1 one or more flow or blocks Figure 1 one or more flow or blocks

[0080] These computer program instructions can also be stored in a computer- readable memory that can direct a computer or other programmable data processing apparatus to function in a particular manner, such that the instructions stored in the computer-readable memory produce an article of manufacture including instructions which implement the function specified in the flowchart block or blocks. Figure 1 one or more flow or blocks Figure 1 one or more flow or blocks

[0081] The computer program instructions can also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer-implemented process such that the instructions which execute on the computer or other programmable apparatus provide steps for implementing the functions specified in the flowchart block or blocks. Figure 1 one or more flow or blocks Figure 1 one or more flow or blocks

[0082] Obviously, numerous modifications and variations of the present application are possible in light of the above teachings. It is therefore to be understood that within the scope of the

[0083] Those skilled in the art will appreciate that the application described herein is susceptible to variations and modifications other than those specifically described. It is to be understood that the application includes all such variations and modifications which fall within the spirit and scope of the present application.

Claims

1. A satellite low-brightness design and analysis method based on a satellite thermal control model, characterized in that, The application relates to a temperature-luminance integrated design method for a satellite. According to the temperature-luminance integrated design condition and the working condition parameters thereof, and according to the external heat flow level and the illumination level, satellite surface thermal control and low luminance design is carried out. According to the result of the satellite surface thermal control and low luminance design, a satellite thermal control model is established. According to the temperature-luminance integrated design condition and the satellite thermal control model, satellite thermal control feasibility analysis and satellite luminance analysis are carried out in sequence, and the analysis results are compared with the thermal control requirements and the low luminance requirements of the satellite to confirm whether the indexes are met; when the indexes are not met, satellite surface thermal control and low luminance design is re-performed until the requirements are met. The satellite surface thermal control and low luminance design comprises the following steps.

2. The satellite low-brightness design and analysis method based on a satellite thermal control model according to claim 1, characterized in that, For a carbon fiber skin structure plate, the skin is used as a low luminance heat dissipation surface. For an aluminum skin structure plate, black paint is sprayed or black film is pasted at the position of the heat dissipation surface to realize low luminance design of the heat dissipation surface. For a satellite surface that is not a heat dissipation surface, a multi-layer surface film is used for coating, and a double-layer perforated black surface film is used for staggered hole installation. For other positions and devices on the satellite surface, a thermal control black paint coating, a pasted black surface film or a multi-layer black surface film coating is used for low luminance design, and a double-layer perforated black surface film is used for staggered hole installation when a multi-layer black surface film is used. The multi-layer surface film is a black polyimide film, and the solar absorption ratio of the film surface is 0.78 or above. The establishment of the satellite thermal control model comprises the following steps.

3. The satellite low-brightness design and analysis method based on a satellite thermal control model according to claim 2, characterized in that, The thermal control feasibility analysis comprises the following steps.

4. The satellite low-brightness design and analysis method based on a satellite thermal control model according to claim 2, characterized in that, The satellite luminance analysis comprises the following steps.

5. The satellite low-brightness design and analysis method based on a satellite thermal control model according to claim 4, characterized in that, In the thermal analysis model, a perception surface at different positions is established, the satellite albedo energy obtained on the perception surface is obtained through space external heat flow calculation based on the Monte Carlo and ray tracing algorithms, and the satellite luminance is calculated equivalently. ​ 6. The satellite low-brightness design and analysis method based on a satellite thermal control model according to claim 4, characterized in that, ​ ​ 7. The satellite low-brightness design and analysis method based on a satellite thermal control model according to claim 6, characterized in that, The sensing surface is set to have a material property of a solar absorption ratio of 1, a distance from a satellite thermal control model should be more than 10 times of a satellite scale, an area of the sensing surface should be within a range of 20% of a cross-sectional area of the satellite, and a position of the sensing surface should avoid a solar-satellite connecting line to avoid blocking an effective outer heat flow of the satellite.

8. A computer-readable storage medium storing a computer program, the computer program comprising instructions that, when executed by a computer, cause the computer to perform the method of any one of claims 1-7. The computer program is executed by the processor to implement the steps of the method of any one of claims 1-7. 9.A satellite low-brightness design and analysis device based on a satellite thermal control model, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, and characterized in that: The processor executes the computer program to implement the steps of the method of any one of claims 1-7.

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