Thermal control design method and system for large-dip-angle medium-high-orbit large-power-consumption communication satellite

Abstract

The invention relates to the technical field of satellite thermal control, in particular to a thermal control design method and system for a large-dip-angle medium-and-high-orbit large-power-consumption communication satellite, and the method comprises the steps: obtaining a target orbit precise parameter of a target satellite, and building an orbit external heat flow calculation model based on the target orbit precise parameter in combination with task life; on the basis of the orbit external heat flow calculation model, calculating each surface external heat flow fluctuation amplitude in each attitude mode under a target satellite body coordinate system, and defining a sun-oriented target attitude mode according to each attitude fluctuation amplitude calculation result and a preset multi-constraint condition; determining an equipment dispersion layout strategy and a heat dissipation surface planning strategy based on the target attitude mode; and constructing a target heat transfer path from the equipment to the heat dissipation surface according to the equipment dispersion layout strategy and the heat dissipation surface planning strategy, and formulating a partition heat management strategy. The reliability and adaptability of the satellite thermal control system are improved.

Description

Technical Field

[0001] This disclosure belongs to the field of spacecraft thermal control technology, and in particular relates to a thermal control design method and system for high-inclination, high-power communication satellites in medium-high orbit. Background Technology

[0002] Spacecraft thermal control is a core technology to ensure the reliable operation of satellites and payloads in orbit. Satellites need to collect, transfer and release internal heat in the extreme high and low temperature environment of space to ensure that the equipment is within the required operating temperature range. Failure of the thermal control system will directly lead to a decline in equipment performance, a shortened lifespan, or even mission failure.

[0003] With the rapid growth in communication and navigation demands, high-inclination medium-to-high orbit satellites are developing towards higher power and higher integration. Their thermal control faces three core challenges: severe fluctuations in external heat flow, dense internal heat dissipation, and contradictions between layout and heat dissipation. Traditional thermal control solutions adopt a "passive-first, active-second" strategy, using a combination of multi-layer insulation components (MLI), heat pipes, and electric heaters. However, this approach suffers from significant drawbacks, including reliance on numerous heat pipes coupled across the module to balance the heat load, high system weight, energy consumption from active heating encroaching on payload power, and the need for sufficient heat dissipation surface margins for extreme operating conditions, resulting in severe resource waste.

[0004] Therefore, there is an urgent need for a thermal control design strategy suitable for high-inclination, high-power communication satellites in medium and high orbits, in order to achieve efficient thermal management of such satellites. Summary of the Invention

[0005] To address the aforementioned issues, this disclosure provides a thermal control design method and system for high-power communication satellites in medium-high orbits with large inclination angles. It employs a technical approach of precise modeling of external heat flow, stable attitude selection, collaborative planning of equipment and heat dissipation surfaces, and graded heat transfer and zoned temperature control. This approach effectively reduces the impact of external heat flow fluctuations on satellite thermal control in medium-high orbit environments with large inclination angles, ensures the temperature stability of high-power equipment, and improves the reliability and adaptability of the satellite thermal control system.

[0006] Firstly, this disclosure provides a thermal control design method for high-inclination, high-power communication satellites in medium-to-high orbits, including: Obtain the precise orbital parameters of the target satellite, and establish an external heat flow calculation model based on the precise orbital parameters and mission lifetime. The external heat flow calculation model is used to calculate the external heat flow fluctuation amplitude of each surface in each attitude mode under the target satellite body coordinate system, so as to define the target attitude mode for sun orientation based on the calculation results of each attitude fluctuation amplitude and the preset multi-constraint conditions. Based on the target attitude pattern, determine the device distribution layout strategy and heat dissipation surface planning strategy; Based on the device distributed layout strategy and the heat dissipation surface planning strategy, a target heat transfer path from the device to the heat dissipation surface is constructed, and a zoned thermal management strategy is formulated.

[0007] Furthermore, An external heat flux calculation model is established based on the precise parameters of the target orbit and the mission lifetime, specifically including: Extract the orbital altitude, orbital inclination, orbital period, right ascension of the ascending node, and angle of anomaly corresponding to the target orbit, and use them as the precise parameters of the target orbit; Based on the precise parameters of the target orbit and the mission lifetime, the time-varying external heat flux experienced by each surface of the satellite in its body coordinate system during its on-orbit operation is calculated. The time-varying external heat flux is the direct solar radiation heat flux.

[0008] Furthermore, Based on the aforementioned orbital external heat flow calculation model, the fluctuation amplitude of external heat flow on each surface of the target satellite in each attitude mode is calculated, specifically including: Based on the above orbital heat flow calculation model, the real-time direct solar radiation heat flow experienced by the target satellite in each attitude and each surface period under the coordinate system of the target satellite body is determined. Based on the aforementioned real-time solar direct radiation heat flow, surface heat flow variation diagrams for each attitude are plotted, and the fluctuation amplitude is determined by analyzing the variation diagrams.

[0009] Furthermore, Based on the calculation results of various attitude fluctuation amplitudes and the preset multi-constraint conditions, a target attitude mode for sun orientation is defined, specifically including: Set preset task load constraints, energy constraints, and attitude control constraints; Based on the aforementioned pre-set constraints, the sun-oriented attitude mode with the smallest total fluctuation amplitude of external heat flow in the target satellite body coordinate system is selected.

[0010] Furthermore, Based on the target posture pattern, a distributed device layout strategy is determined, specifically including: Based on the real-time operating power of a single device, it is compared with a preset power threshold, and high-power single devices are selected based on the comparison results. A whole-satellite thermal model is established using thermal analysis software. Stable external heat flow data under the target attitude mode is input, and the high-power single units are distributed in a distributed manner.

[0011] Furthermore, The heat dissipation surface planning strategy is determined based on the target attitude pattern, specifically including: Based on the target attitude pattern, the main heat dissipation candidate surface, the auxiliary heat dissipation surface, and the non-heat dissipation surface are determined. Apply a high-stability heat dissipation coating to all or most of the outer surface of the main heat dissipation candidate surface; A high-emissivity white paint coating is applied to the outer side of the auxiliary heat dissipation surface; The non-heat-dissipating surface is covered with a multi-layer heat insulation component.

[0012] Furthermore, Based on the device distribution layout strategy and the heat dissipation surface planning strategy, a target heat transfer path from the device to the heat dissipation surface is constructed, specifically including: For the equipment inside the cabin, a primary heat transfer path is constructed by covering the cabin plate with an orthogonal stacked pre-embedded heat pipe network. For external equipment, external heat pipes are used to conduct its heat to the main heat dissipation candidate surface, thus constructing a secondary heat transfer path.

[0013] Furthermore, Develop a zoned thermal management strategy, specifically including: The cabin is divided into several independent thermal zones based on the thermal characteristics of the equipment. Set a corresponding temperature threshold for each independent hot zone; Thin-film electric heaters and thermistors are arranged in each independent hot zone. Temperature control is designed based on temperature thresholds according to the temperature index and thermal inertia requirements of each independent hot zone to determine the zoned thermal management strategy.

[0014] Furthermore, The design incorporates temperature threshold control based on the temperature parameters and thermal inertia requirements of each independent thermal zone, specifically including: Analyze the heat load characteristics and temperature change patterns of any of the independent hot zones, and set PID control parameters based on the heat load characteristics and temperature change patterns; Set a temperature control threshold. When the temperature of an independent hot zone is lower than its corresponding temperature threshold, output a heating command to start the thin-film electric heater in that zone.

[0015] Secondly, based on the same inventive concept, this disclosure provides a thermal control design system for a high-inclination, high-power communication satellite in a medium-to-high orbit, the system comprising: The model building module is used to obtain the precise parameters of the target satellite's target orbit, and to build an external heat flow calculation model based on the precise parameters of the target orbit and the mission lifetime. The attitude definition module is used to calculate the surface heat flow fluctuation amplitude of the target satellite in each attitude mode under each attitude mode based on the orbital external heat flow calculation model, so as to define the target attitude mode for sun orientation according to the calculation results of each attitude fluctuation amplitude and the preset multi-constraint conditions. The strategy planning module is used to determine the device distribution layout strategy and heat dissipation surface planning strategy based on the target posture pattern; The path construction module is used to construct the target heat transfer path from the device to the heat dissipation surface based on the device distribution layout strategy and the heat dissipation surface planning strategy, and to formulate a zoned thermal management strategy.

[0016] Compared with the prior art, this disclosure has the following advantages: 1. This disclosure fundamentally eliminates most of the compensatory heating requirements due to drastic changes in the external thermal environment by providing stable external heat dissipation conditions, while simplifying thermal control design and control logic. Calculations show that active heating power consumption under such operating conditions can be reduced, and the saved energy can be used to extend payload operating time or support other on-board functions.

[0017] 2. This disclosure reduces the reliance on complex internal radiation heat transfer and combined heat pipe networks coupled between different modules for heat dissipation. Thermal design can focus more directly on efficiently transferring heat from the source to a stable heat dissipation surface, thus simplifying the system architecture and reducing the complexity of satellite installation due to externally attached heat pipes between different modules, thereby reducing weight. Furthermore, the orthogonal grid-like pre-embedded heat pipe layout used in this disclosure achieves comprehensive, dead-angle-free coverage of the heat dissipation panel area compared to traditional U-shaped or serpentine single-path layouts. This layout greatly enhances the panel's in-plane temperature uniformity and lateral heat diffusion efficiency, significantly reducing the temperature of local hot spots, and maximizing the heat dissipation capacity and efficiency per unit area of ​​the heat dissipation panel. Ultimately, this results in a smaller heat dissipation surface area and fewer heat pipes required to achieve the same heat dissipation performance, achieving a higher heat dissipation density per unit area (W / m²). 2 ) and heat dissipation efficiency per unit weight (W / kg).

[0018] 3. This disclosure reduces the reliance on a large number of electric heaters and their control circuits, which is equivalent to reducing the potential single point of failure in the system. At the same time, it simplifies the complex heat pipe network (especially eliminating the coupling heat pipes across the compartments), and the inherent path redundancy of the orthogonal heat pipe network (the local failure of a single heat pipe does not affect the overall function) improves the inherent reliability of the entire satellite thermal control system.

[0019] 4. This disclosure ensures that the selected heat dissipation surface is always in optimal heat dissipation condition (for deep cold spaces), and maximizes and stabilizes its heat dissipation capacity by optimizing the heat dissipation layout. It also allows for more precise and minimal design of the heat dissipation surface area, thereby reducing structural weight.

[0020] Other features and advantages of this disclosure will be set forth in the description which follows, and will be apparent in part from the description, or may be learned by practicing the disclosure. The objects and other advantages of this disclosure may be realized and obtained by means of the structures pointed out in the description, claims and drawings. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of this disclosure or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this disclosure. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0022] Figure 1 A flowchart illustrating a thermal control design method for a high-inclination, high-power communication satellite in medium-high orbit according to an embodiment of the present disclosure is shown. Figure 2 A schematic diagram of a satellite's sun-orientation attitude according to an embodiment of the present disclosure is shown; Figure 3 A comparison graph showing the change curve of external heat flow over time of a heat dissipation surface according to an embodiment of the present disclosure with that of a conventional method is shown; Figure 4 A schematic diagram of an orthogonal stacked embedded heat pipe network structure according to an embodiment of the present disclosure is shown; Figure 5 A schematic diagram of an external heat pipe structure for a high heat flux density single unit inside a cabin, according to an embodiment of the present disclosure, is shown. Figure 6 A functional block diagram of a satellite thermal control system according to an embodiment of the present disclosure is shown; Figure 7 A schematic diagram illustrating the heat flow path principle of a satellite thermal control system according to an embodiment of the present disclosure is shown. Figure 8 A flowchart illustrating the design of a whole-satellite thermal control system according to an embodiment of the present disclosure is shown. Detailed Implementation

[0023] To make the objectives, technical solutions, and advantages of the embodiments of this disclosure clearer, the technical solutions of the embodiments of this disclosure will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this disclosure, and not all embodiments. Based on the embodiments of this disclosure, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this disclosure.

[0024] Figure 1 A flowchart illustrating a thermal control design method for a high-inclination, high-power communication satellite in a medium-to-high orbit according to an embodiment of this disclosure is shown, as follows: Figure 1 As shown in the figure, the thermal control design method for high-inclination, high-power communication satellites in medium-high orbit according to this disclosure includes, S1, obtain the precise parameters of the target satellite's target orbit, and establish an external heat flow calculation model based on the precise parameters of the target orbit and the mission lifetime; In this embodiment of the disclosure, step S1 specifically includes: S11, extract the orbital altitude, orbital inclination, orbital period, right ascension of the ascending node and angle of anomaly corresponding to the target orbit, and use them as the precise parameters of the target orbit; S12, based on the precise parameters of the target orbit and the mission lifetime, calculate the time-varying external heat flux experienced by each surface of the satellite in its body coordinate system during its on-orbit operation. The time-varying external heat flux includes direct solar radiation heat flux.

[0025] In this embodiment of the disclosure, the precise parameters of the target orbit of the satellite are obtained, including but not limited to: orbital altitude (H), which typically ranges from 8000km to 25000km; orbital inclination (i), which typically ranges from 45° to 90°; orbital period, right ascension of the ascending node, and mean apogee angle, etc.

[0026] In this embodiment of the disclosure, the mission lifespan is typically 12 to 15 years.

[0027] S2, Based on the orbital external heat flow calculation model, calculate the periodic fluctuation amplitude of external heat flow on each surface of each attitude in the target satellite body coordinate system, so as to select the most stable solar orientation attitude mode under multiple constraints such as satellite energy, payload mission, and attitude control. In this embodiment of the disclosure, step S2 specifically includes: S21, Based on the orbital heat flow calculation model, determine the real-time direct solar radiation heat flow experienced by each surface period in the target satellite body coordinate system; S22, draw a variation diagram based on several of the real-time direct solar radiation heat flows, and analyze the variation diagram to determine its fluctuation amplitude; S23 defines the task load constraints: the attitude must satisfy the requirements of camera imaging to the ground and antenna communication to the ground, and the surface with the smallest external heat flow fluctuation should not be occupied by the task load.

[0028] S24 determines the energy constraint: this attitude ensures that the solar array is aligned with the sun, meeting the energy needs of the entire satellite.

[0029] S25 defines the attitude control constraints: the attitude should be easy to achieve and control, the maneuver process should be simple and energy-efficient; S26. Based on the fluctuation amplitude, determine the sun-oriented attitude mode that minimizes the total fluctuation amplitude of external heat flow under the target satellite body coordinate system, satisfying all constraints.

[0030] In the embodiments disclosed herein, the infrared radiation heat flux and albedo heat flux received by medium and high orbit satellites from the Earth are relatively small and are generally not considered.

[0031] In this embodiment of the disclosure, the direct solar radiation heat flux is calculated as follows: When a satellite's orbital altitude is lower than that of a geostationary orbit, sunlight can be considered as uniform parallel light, with a radiant intensity equal to the solar constant S = 1367 W·m. -2 Then the heat flux from solar radiation experienced by any surface element A on the outer surface of the satellite is:

[0032] make Then there is , This is called the solar radiation angle coefficient; In the embodiments of this disclosure, the satellite is a non-spin-stabilized satellite; therefore, the parameters in the expression for its external space heat flow are calculated as follows: Solar radiation angle coefficient ,when When this occurs, it indicates that the outer surface element is not exposed to sunlight, and can be... Recorded as 0, when the satellite is in the Earth's shadow, it cannot receive the external heat flow from solar radiation, therefore all external surface elements are... All are 0; In this embodiment of the disclosure, based on the target satellite's orbital period (e.g., a typical period of about 12 hours in a high-inclination medium-high orbit) and mission lifespan (12-15 years), real-time heat flow data of each surface (±X, ±Y, ±Z) in the satellite's body coordinate system within a complete orbital period (covering key phases such as perigee, apogee, and shadow area) and an annual period (covering the maximum variation range of the solar illumination angle β, such as -78.5° to +78.5° in a 55° inclination orbit) are extracted using an extraorbital heat flow calculation model. This forms a continuous heat flow time series sample (sample intervals are no more than 10 minutes to ensure the capture of dynamic changes in heat flow).

[0033] In this embodiment of the disclosure, the first fluctuation amplitude is: based on the selected solar direct radiation heat flux time series sample, a first variation graph is plotted (the horizontal axis is time / orbital phase, and the vertical axis is the heat flux value, in W / m). 2 ); Identify and extract the maximum value (Φ1_max) and minimum value (Φ1_min) of direct solar radiation heat flux within the cycle from the first variation diagram, and calculate the extreme value difference ΔΦ1=Φ1_max-Φ1_min as the core reference for the first fluctuation amplitude; Simultaneously, the standard deviation (σ1) of the heat flow sequence is calculated to verify the degree of fluctuation dispersion and ensure that the extreme value difference can truly reflect the periodic fluctuation characteristics.

[0034] In this embodiment of the disclosure, the solar orientation attitude mode that satisfies the constraints with the smallest total fluctuation amplitude of external heat flow specifically includes: calculating the real-time direct solar radiation heat flow of each surface within the same period based on the orbital external heat flow calculation model, and obtaining the real-time external heat flow value of each surface; extracting the maximum value (Φ) of the total external heat flow of each surface. total_max ) and minimum value (Φ total_min ), calculate the extreme value difference ΔΦ total =Φ total_max -Φ total_min The total fluctuation amplitude of external heat flow on each surface is used as the reference value; the ΔΦ values ​​of the six surfaces (±X, ±Y, ±Z) under various attitude modes satisfying the constraints are compared. total Filter out ΔΦ total Minimal pose mode.

[0035] The process of determining the satellite's flight attitude and main heat dissipation surface is a collaborative decision-making method: First, based on the satellite's orbital parameters and geometric model, the full-cycle external heat flow data of each candidate module surface under various candidate attitude modes is calculated, and its fluctuation characteristics are analyzed; then, from the perspective of optimal thermal control, the attitude-surface combination with the most stable external heat flow is selected; finally, this preferred scheme is subjected to a system-level compromise with the requirements of multiple disciplines such as satellite energy, payload mission, and attitude control, and the flight attitude and its corresponding main heat dissipation surface that can both meet the main mission constraints and provide a stable heat dissipation environment for the thermal control system are finally determined.

[0036] In this embodiment of the disclosure, the specific implementation method of the sun-oriented attitude mode is defined as follows: (Yaw Maneuver): The satellite's yaw axis (Z-axis) is controlled to point towards the Earth's center, while the roll axis (X-axis) is along the direction of its orbital velocity. By controlling the satellite to perform a yaw maneuver around the Z-axis, the ±Y or +X planes are kept away from direct sunlight and always facing deep space. This mode requires coordinated control of the solar array's drive mechanism to ensure energy supply. Regardless of the mode used, the control objective is to stably maintain the angle (θ) between the selected plane normal direction and the solar vector within ±10°, preferably within ±5°. This pointing accuracy can be achieved through high-precision star sensors and control algorithms.

[0037] Figure 2 A schematic diagram of a satellite's sun-orientation attitude according to an embodiment of this disclosure is shown. See also: Figure 2As shown, the right-handed Cartesian coordinate system of the satellite body is clearly marked (+X points to the forward flight side along the orbital tangent, +Z defines the orbital spatial attitude along the orbital normal, and +Y is orthogonal to both to form the attitude control reference axis). The solar vector, with an arrow indicating the direction of solar incidence, and the Earth vector, with an arrow pointing to the Earth's center of mass, are marked. The ±Y plane of the satellite is clearly defined as a stable heat dissipation surface. This attitude design, through the coordinated control of the yaw of the satellite around the +Z axis and the single-axis drive of the solar array, ensures that the ±Y heat dissipation surface continuously avoids direct sunlight (the angle of light received is small in the illustrated attitude), while ensuring that the solar array tracks the solar vector to obtain energy.

[0038] Figure 3 A comparison graph showing the change in external heat flow over time of a heat dissipation surface according to an embodiment of the present disclosure with that of a conventional method is shown. See also: Figure 3 It is known that under traditional orthogonal flight attitude, all six surfaces of the cabin experience drastic changes in external heat flow, with no effective and stable heat dissipation windows. However, under the fully dynamic deflection attitude disclosed in this paper, the external heat flow on the +X and ±Y surfaces is almost zero and extremely stable, meeting the conditions for becoming good heat dissipation surfaces. The figure clearly shows that under orthogonal flight mode (solid line), the heat flow, especially on the ±Y surfaces, fluctuates drastically, exceeding 300 W / m at extreme angles. 2 On the other side, the heat flow drops sharply to zero, exhibiting a strong cycle of external heat flow changes. The fully dynamic deflection mode (dashed line) makes the heat flow on all surfaces exceptionally stable through attitude adjustment. In particular, the external heat flow on the ±Y and +X surfaces is almost zero, effectively eliminating heat flow peaks, greatly improving the thermal environment stability of the satellite, significantly reducing the design difficulty of the thermal control system, and improving the on-orbit reliability of the equipment.

[0039] In this embodiment, quasi-static attitude control can also be achieved through slow, rotating rotation of the satellite. This approach does not require the satellite to maintain a precisely fixed attitude; instead, it controls the satellite to rotate continuously and slowly (e.g., 360° per orbital cycle) around its axis pointing towards the sun (e.g., the +Y axis). Simultaneously, by controlling the rotation phase, it is ensured that the surfaces requiring heat dissipation (e.g., the ±Y surfaces) are always positioned away from the sun and Earth during its rotation. Although the satellite rotates, from a thermal perspective, each of its heat dissipation surfaces experiences the exact same external thermal environment at a given phase. As long as the rotation is uniform and continuous, it still provides a statistically stable thermal environment for the satellite in terms of time averaging. Heat can be transferred to the surfaces currently in the cooling phase via a heat pipe network.

[0040] S3, determine the device distribution layout strategy and heat dissipation surface planning strategy based on the target posture mode; In this embodiment of the disclosure, step S3 specifically includes: S31: Based on the real-time operating power of a single device, compare it with a preset power threshold, and select high-power single devices based on the comparison results; S32, Use thermal analysis software to establish a whole-satellite thermal model, input stable external heat flow data under the target attitude mode, and distribute the high-power single units.

[0041] The high-power individual units are distributed and arranged in a decentralized manner, specifically as follows: Based on the overall satellite thermal model, stable external heat flow data under the target attitude mode is input for simulation calculation; the temperature field and heat flow distribution on the heat dissipation surface in the simulation results are analyzed; if there are local heat accumulation areas, the high-power individual units in the accumulation areas are adjusted to the area of ​​the compartment with sufficient heat dissipation capacity as shown in the simulation results, so as to minimize the coupling of heat pipes between the panels; the above simulation and layout adjustment process is repeated until the overall satellite temperature field meets the requirements and the heat flow distribution is balanced, and finally the layout coordinates of all devices and the corresponding heat pipe network optimization scheme are output.

[0042] In this embodiment of the disclosure, establishing a whole-satellite thermal model using thermal analysis software includes: The specific steps are as follows: 1. Geometric Modeling and Discretization: Based on the 3D model of the satellite's overall assembly layout, its simplified geometric shape is extracted. The various physical panels, equipment, and structural components of the satellite are discretized into a thermal model consisting of nodes and a network. Nodes represent small units with uniform temperature, while the network represents heat exchange paths between units, such as conduction and radiation. This model should include all major heat sources, heat dissipation surfaces, internal structures, and their assembly relationships.

[0043] 2. Assignment of thermophysical property parameters: Each element in the model is assigned its realistic thermophysical properties. These include: heat capacity (describing the element's ability to store heat); thermal conductivity (describing the material's ability to conduct heat); and surface thermo-optical properties (solar absorptivity α and hemispherical emissivity ε).

[0044] 3. Define boundary conditions: The heat consumption (power value and operating mode) of each unit is used as an internal heat source and applied to the corresponding equipment node; the external space heat flow is applied to the corresponding satellite external surface node; the thermal conductivity between the equipment and the mounting plate (through contact thermal conductivity or thermally conductive filler), between the mounting plate and the pre-embedded heat pipe, and between each structural component is defined; the radiation angle coefficient between each surface inside the satellite and between the external surface and the space environment is calculated (automatically calculated by professional software using the Monte Carlo method) to establish a radiative heat exchange network.

[0045] The input data is: 1. Geometric data: Simplified 3D model of the satellite assembly; dimensions and area of ​​each component.

[0046] 2. Thermal properties: surface optical properties (solar absorptivity α, hemispherical emissivity ε); material thermal conductivity k, density, specific heat capacity (used to calculate heat capacity C).

[0047] 3. Internal heat source data: heat consumption (W) and operating mode (continuous, intermittent, peak) of each individual device.

[0048] 4 Boundary condition data: thermal conductivity between each device and the mounting plate, between the mounting plate and the embedded heat pipe, and between each structural component.

[0049] 5. Orbit and attitude parameters: orbit height, tilt angle, time; attitude mode.

[0050] The output data is: 1. High-fidelity parametric thermal model: A file that can be used for NX SST calculations.

[0051] 2. Initial temperature field distribution: list of node temperature data and temperature contour map.

[0052] 3. Heat flux distribution diagram: Heat flux density distribution cloud map on the heat dissipation surface.

[0053] 4. Performance data: Temperature change curves of key equipment / nodes over time, operating temperature and heat transfer load of heat pipes, and power requirements of heaters.

[0054] In this embodiment of the disclosure, the high-power single unit has a heat flux density > 0.5 W / cm². 2 Or high heat flux density, high heat dissipation equipment with heat dissipation >100W (such as traveling wave tube amplifiers, solid-state power amplifiers, digital processing units).

[0055] In this embodiment of the disclosure, step S3 further includes: S33, determine the main heat dissipation candidate surface, auxiliary heat dissipation surface, and non-heat dissipation surface based on the target attitude mode; S34, apply a high-stability heat dissipation coating to all or most of the outer side of the main heat dissipation candidate surface; S35, a high emissivity white paint coating is applied to the outer side of the auxiliary heat dissipation surface; S36, the non-heat-dissipating surface is covered with a multi-layer heat insulation component.

[0056] In this embodiment, the main area outside the main heat dissipation candidate surface refers to the main area of ​​the surface used for heat dissipation, excluding non-heat dissipation functional areas such as necessary structural interfaces and sensor mounting positions. The coverage area needs to meet the emission requirements of the main heat consumption of the entire satellite, and usually accounts for more than 70% of the total area of ​​the surface (determined in conjunction with the heat dissipation load calculated by thermal simulation).

[0057] In this embodiment of the disclosure, a secondary surface mirror (OSR) is laid on all or most of the outer area of ​​the main heat dissipation surface. The thermo-optical performance parameters of the OSR meet the requirements of absorptivity α ≤ 0.25 at the end of the solar lifetime and hemispherical emissivity ε ≥ 0.79, so as to achieve efficient radiative heat dissipation and reduce solar heat absorption. The auxiliary heat dissipation surface includes the +X surface (when it is not the main heat dissipation surface) and a partial ±Z surface. A high emissivity white paint coating is applied to the outside of the auxiliary heat dissipation surface. The hemispherical emissivity ε of the white paint coating is ≥0.9, which serves as a supplement to the heat dissipation of the main heat dissipation surface. All external surfaces of the satellite, except for the main heat dissipation surface and the auxiliary heat dissipation surface, are non-heat dissipation surfaces. The non-heat dissipation surfaces are covered with a multi-layer thermal insulation component (MLI). The MLI consists of 10-15 layers of aluminized polyimide film to isolate external heat flow interference and maintain a stable internal thermal environment.

[0058] S4. Construct the target heat transfer path from the equipment to the heat dissipation surface based on the equipment distributed layout strategy and the heat dissipation surface planning strategy, and formulate a zoned thermal management strategy.

[0059] In this embodiment of the disclosure, step S4 specifically includes: S41, for the equipment inside the cabin, a primary heat transfer path is constructed by covering the cabin plate with an orthogonal stacked pre-embedded heat pipe network. For S42, external heat pipes are used to conduct heat to the main heat dissipation candidate surface to construct a secondary heat transfer path for external equipment.

[0060] In this embodiment, for devices directly mounted on the inner side of the stable heat dissipation surface, an orthogonal stacked pre-embedded heat pipe network is used to achieve surface heat diffusion. The layout of orthogonal heat pipes is more flexible. Compared with U-shaped heat pipes, which require consideration of turning radius layout limitations for heat expansion and heat dissipation, and because bending can lead to a decrease in heat transfer capacity and weaken the heat dissipation of high-power devices, there will be certain areas on the heat dissipation surface that are not covered by heat pipes, resulting in low-temperature cold zones, which will reduce the heat dissipation efficiency of the surface to a certain extent.

[0061] Specifically, Figure 4 A schematic diagram of an orthogonal stacked embedded heat pipe network structure according to an embodiment of the present disclosure is shown. See also: Figure 4 As shown, in the manufacturing process of this aluminum alloy honeycomb panel, multiple high-strength channel heat pipes are orthogonally arranged along the X and Y directions of the panel at intervals of 150mm-200mm, forming a grid-like channel. They are also arranged in layers along the thickness direction, with overlapping heat pipes filled with expanding foam and bonded to the upper and lower skins to form a unified whole. This structure significantly reduces the in-plane lateral thermal resistance of the panel, allowing the surface temperature difference ΔT to be controlled within 3-5℃, providing a highly uniform temperature mounting platform for core equipment.

[0062] In this embodiment, for external equipment (high-power single units that cannot be directly installed on the inner side panel of the main heat dissipation candidate surface), where heat distribution is uneven and a large amount of heat is concentrated at the top, an external heat pipe network is used. The heat pipe paths are carefully optimized (although there are bends, efficiency loss is minimized by optimizing the bending radius) to "transport" the heat to a stable heat dissipation surface. For example, the heat from the phased array antenna XX equipment is conducted to the heat dissipation surface through a specially designed external heat pipe loop. For internal high heat flux density single-unit XX equipment, a dual-path parallel heat conduction method can also be used. This involves pre-embedded orthogonal heat pipes at the bottom of the unit and external heat pipes at the top, effectively reducing heat accumulation due to internal thermal resistance and achieving rapid heat dissipation.

[0063] Figure 5 A schematic diagram of an external heat pipe structure for a high heat flux density single unit inside a cabin, according to an embodiment of the present disclosure, is shown. See also: Figure 5 The diagram shows the bidirectional thermal coupling of a high-power single unit inside the cabin. For heat dissipation at the top of the single unit that cannot be directly connected to the installation heat dissipation surface, an external heat pipe is used to transport the heat to the heat dissipation surface (such as the phased array TR component of the single unit outside the cabin, where the heat dissipation is at the top of the single unit).

[0064] In this embodiment of the disclosure, the heat pipe of the primary heat transfer path is a high-strength aluminum-ammonia channel heat pipe with a diameter of 8mm or 10mm selected according to the heat load of the cabin plate. The heat pipes are generally orthogonally stacked at a spacing of 150mm to 200mm to ensure that the temperature gradient inside the cabin plate is less than 3-5℃. External heat pipes in the secondary heat transfer path include flexible heat pipes or axially channeled heat pipes, with a bending radius of not less than 5 times the pipe diameter (e.g., a 6mm diameter heat pipe with a bending radius ≥ 30mm). The external heat pipe terminals are connected to the pre-embedded heat pipe network on the main heat dissipation candidate surface via thermally conductive silicone grease (thermal conductivity of 800 to 1000 W / (m²)). 2 •K)) connection, with thermal resistance controlled within 0.1℃ / W; The thermally conductive filler for the parallel heat transfer path is high thermal conductivity silicone grease or indium foil with a thermal conductivity ≥10W / (m•K). The contact thermal resistance between the bottom of the unit and the mounting plate is ≤0.05℃ / W. The top external heat pipe and the unit casing are filled with thermally conductive silicone grease and fixed with screws to ensure flatness and good thermal contact.

[0065] In this embodiment of the disclosure, step S4 further includes: S43, the cabin is divided into several independent hot zones according to the thermal characteristics of the equipment; S44 sets the corresponding temperature threshold for each independent hot zone; S45, in each independent hot zone, a thin-film electric heater and a thermistor are arranged, and the temperature is controlled by a temperature threshold based on the temperature index and thermal inertia requirements of each independent hot zone to determine the zoned thermal management strategy.

[0066] In this embodiment, the partitioning is based on the principle of arranging single units with large heat capacity and high power density on the same mounting surface as much as possible with single units with low power heating and a wide operating temperature range, thereby strengthening the thermal coupling between them.

[0067] In this embodiment of the disclosure, a dedicated temperature threshold is set for each independent hot zone, and the temperature threshold is set according to the minimum operating limit of a single unit in that hot zone.

[0068] In this embodiment of the disclosure, step S45 specifically includes: Analyze the heat load characteristics and temperature change patterns of any of the independent hot zones, and set PID control parameters based on the heat load characteristics and temperature change patterns; Set a temperature control threshold. When the temperature of an independent hot zone is lower than its corresponding temperature threshold, output a heating command to start the thin-film electric heater in that zone.

[0069] In this embodiment of the disclosure, the preset power is 60% of the heater's maximum rated power.

[0070] In this embodiment of the disclosure, the PID needs to be configured with temperature control algorithm settings such as PID parameters based on the temperature gradient.

[0071] Figure 6 For illustrating a functional block diagram of a satellite thermal control system according to an embodiment of this disclosure, see [link to documentation]. Figure 6As shown, it includes: 1. Input and top-level control (top layer): First, the satellite's orbital parameters (such as altitude, inclination, etc.) and thermal control parameters (such as equipment heat consumption, mission lifespan, etc.) are collected. Based on these parameters, an external heat flow analysis is conducted (calculating the periodic changes in heat flow such as solar radiation, Earth's infrared radiation, and Earth's albedo). Finally, a sun-oriented attitude mode is defined, and by controlling the satellite's yaw and roll axis pointing, the main heat dissipation surface is stably aligned with the deep cold space, providing a foundation for a "stable heat dissipation environment" for subsequent thermal control design. 2. Attitude control implementation (second layer): This step is the core link of the "three-level collaboration". It ensures attitude accuracy through multi-dimensional means, using a high-precision star sensor (to measure satellite attitude), an attitude control computer (to process attitude data), and a reaction flywheel / thruster (to perform attitude adjustments) to achieve precise control of the satellite's attitude. Ultimately, it ensures that the main heat dissipation surface continuously faces the cold space, creating stable external conditions for thermal control from the "attitude level". 3. Equipment Layout Strategy (Third Layer): Based on a stable attitude pattern, a refined design of equipment layout is carried out, which is divided into two categories of core equipment layout logic: high heat flux density / high heat consumption equipment is given priority to be placed on the inner side of the main heat dissipation surface (utilizing the efficient heat dissipation capacity of the main heat dissipation surface to quickly dissipate the heat of the equipment); conventional equipment is combined with thermal simulation analysis to carry out "heat load matching and dispersion layout" (avoiding local heat accumulation and balancing the heat distribution of the entire satellite). 4. Thermal Control and Management Implementation (Fourth Layer): This is the "execution layer" of thermal control design, focusing on three main areas: heat transfer path, heat dissipation surface, and temperature control strategy. Heat transfer path construction is achieved through "single-unit thermal conductivity design (such as high thermal conductivity filler) + parallel heat pipe network (pre-embedded / external heat pipes)" to achieve efficient heat transfer from equipment to the heat dissipation surface. Precise heat dissipation surface control is achieved by applying secondary surface mirrors (OSR) to the main heat dissipation surface, applying high emissivity white paint to the auxiliary heat dissipation surface, and covering non-heat dissipation surfaces with multi-layer insulation components (MLI) to differentiate and improve heat dissipation / insulation efficiency. Zoned temperature control is implemented by dividing the satellite cabin into multiple independent hot zones, using "zone heaters + temperature sensors + temperature upper and lower limit switches" to achieve precise temperature control of different hot zones (matching the temperature indicators and thermal inertia of each zone). 5. Final Goal (Lowest Layer): Through the three-level coordination of "input control → attitude assurance → equipment layout → thermal control execution," the overall satellite thermal environment is stabilized, ensuring that the equipment operating temperature meets requirements and guaranteeing reliable on-orbit operation of the satellite. It clearly demonstrates the core architecture of the system-level collaborative design method proposed in this disclosure. The workflow of the thermal control system mainly includes three stages: orbital environment input and top-level attitude decision-making, core execution process, and the final output of a stable temperature environment. The entire scheme follows the three-level collaborative design concept of "attitude-layout-heat transfer", actively creating a stable heat sink through top-level attitude control, and on this basis, optimizing the equipment layout at the middle level and designing efficient heat transfer at the bottom level.

[0072] Figure 7A schematic diagram illustrating the heat flow path principle of a satellite thermal control system according to an embodiment of this disclosure is shown. See also: Figure 7 As shown, the high-heat-consuming equipment inside the satellite platform efficiently transfers the large amount of heat it generates to a dedicated main heat dissipation surface (±Y-side panel) through heat pipe networks and other heat conduction paths embedded within the panels. This surface is covered with OSR (Optical Sealing Reflector) and faces the deep cold space to achieve maximum radiative heat dissipation. The remaining auxiliary heat dissipation surfaces are covered with white paint. Meanwhile, the other surfaces of the satellite are covered with multi-layer thermal insulation material (MLI) to isolate them from the external thermal environment. Through the aforementioned attitude control, the main heat dissipation surface continuously avoids thermal interference from the sun and Earth, stably facing the cold cosmic background, thus constructing a highly efficient and reliable integrated thermal management system based on the logic of "heat collection – centralized transmission – directional radiation".

[0073] Figure 8 A flowchart illustrating the design of a satellite thermal control system according to an embodiment of this disclosure is shown. See also: Figure 8 As shown, it includes input and core judgment: Input: First, identify high heat-dissipating individual units on the satellite (such as traveling wave tube amplifiers with high heat flux density and high heat dissipation).

[0074] Key assessment: Determine whether the high heat-consuming unit can be directly placed inside the main heat dissipation compartment (the main heat dissipation compartment is the core area for satellite radiation and heat dissipation; being close to it allows for more efficient heat dissipation).

[0075] Path 1: Cannot be placed inside the main heat dissipation vent (left dashed box): If a single unit cannot be placed directly inside the main heat dissipation compartment due to layout limitations (such as space conflicts with antennas or other equipment), an auxiliary heat dissipation propulsion and indirect heat transfer strategy will be adopted: Design auxiliary heat dissipation to guide airflow: Plan additional heat dissipation "channels" to guide the heat from the unit to the main heat dissipation area.

[0076] Avoid external structural conflicts: During the design process, avoid external structures (such as antennas and solar panels) from interfering with the antenna's field of view, and ensure that heat dissipation paths and equipment functions do not interfere with each other.

[0077] Verify heat transfer performance: Select contact channel heat pipes / pre-embedded heat pipes to transfer heat, and conduct "fractal tube performance test" to verify whether the heat transfer efficiency of the heat pipes meets the requirements.

[0078] Path 2: Can be placed inside the main heat dissipation bladder (middle dashed box, layout optimization): If a single unit can be directly placed inside the main heat dissipation bladder, thermal control efficiency can be further improved through layout optimization: Prioritize placement inside the main heat dissipation compartment: Utilize the efficient heat dissipation capacity of the main heat dissipation compartment to directly provide "close-range heat dissipation" conditions for individual units.

[0079] Maintain reasonable spacing to avoid heat accumulation: Leave enough space between multiple high-heat-consuming devices to prevent excessive local heat concentration that could lead to overheating.

[0080] Heat dissipation and matching: Distribute part of the heat dissipation to the auxiliary heat dissipation surface to balance the heat load pressure of the main heat dissipation chamber.

[0081] High heat flux is transferred to the embedded heat pipe network: The high heat flux generated by the single unit is transferred to the pre-embedded heat pipe network in the compartment through design. With the help of the high heat conduction characteristics of the heat pipe, the heat is quickly diffused to the main heat dissipation compartment.

[0082] Controllable temperature range: Ultimately, the temperature of a single unit is "adjustable and controllable", and is stabilized within the required operating temperature range.

[0083] Path 3: Can be placed inside the main heat dissipation vent (right dashed box, heat spreader network construction): If a single unit can be directly placed inside the main heat dissipation vent, it can also be optimized from the perspective of "area-like heat dissipation" by constructing a temperature distribution network: Multiple temperature gradient channel heat pipes are pre-embedded inside the main heat dissipation liner: these heat pipes are interconnected to form a "heat conduction network".

[0084] Forming an efficient temperature uniformity network: With the synergistic effect of multiple heat pipes, the temperature inside the main heat dissipation compartment is made more uniform, avoiding local hot spots, and ensuring that the heat of high heat-consuming units can be transferred "evenly and efficiently" to the entire main heat dissipation compartment, and then radiated outwards.

[0085] The thermal control system design flowchart systematically explains the heat dissipation management strategy for high heat-consuming equipment on the satellite: First, the layout is iteratively optimized based on the heat consumption and heat dissipation requirements of the equipment, prioritizing the placement of core heat sources on the inner side of the main heat dissipation surface and balancing the heat load of each compartment through the principle of "heat distribution"; then, a uniform temperature network is constructed by pre-embedding heat pipe channels in the main and auxiliary heat dissipation compartments; for equipment in special locations, external heat pipes with optimized bending radii are used to transfer heat, and finally, all heat is efficiently channeled into the main and auxiliary heat dissipation surfaces through the heat pipe network, forming a closed-loop design process from "heat source management - path optimization - system integration" to ensure the stability and balance of the overall satellite thermal environment.

[0086] To verify the effectiveness of this disclosure, a detailed on-orbit thermal simulation analysis was conducted and compared with traditional methods.

[0087] Experimental subject: A certain type of high-inclination (55 degrees) MEO navigation satellite, with a maximum internal single-unit heat dissipation of 1500W and a heat flux density of 0.8W / cm³. 2 .

[0088] Experimental methods: 1. Establish a high-precision whole-satellite digital thermal model.

[0089] 2. Control group: The satellite was set to a conventional Earth-oriented attitude and the comprehensive thermal control measures described in the background technology were adopted.

[0090] 3. Experimental group: Set the satellite to the sun-oriented attitude (±Y-axis to cryogenic space) as described in this case, and apply all the thermal control design points of this case.

[0091] 4. Run on-orbit thermal simulations for the entire year and extract key parameters.

[0092] The calculation method and results for the judgment conclusion: External heat flow stability: Calculate the standard deviation (σ) of the total external heat flow received by the main heat dissipation surface (±Y surface) during the one-year mission period.

[0093] Control group σ: 150W / m 2 (Violent fluctuations).

[0094] Experimental group σ: <10W / m 2 (Highly stable).

[0095] Temperature fluctuation of heat dissipation surface: Calculate the fluctuation range of the average temperature of the main heat dissipation surface.

[0096] Control group: -35℃ to +45℃.

[0097] Experimental group: -5℃ to +5℃ (significant improvement).

[0098] Active heating energy consumption: The total compensation heating energy (kWh) required for the entire satellite to be in orbit for one year.

[0099] Control group: approximately 1200 kWh.

[0100] Experimental group: approximately 300 kWh (energy consumption reduced by 30%).

[0101] Equipment temperature compliance: Check that the temperature of all equipment is within the specified range (e.g., 0℃ to +40℃) throughout the process.

[0102] Control group: High-power single units require heat dissipation measures under high-temperature conditions and require a large amount of heating under low-temperature conditions.

[0103] Experimental group: The temperature of all equipment remained stable within an excellent range of 15℃ to 30℃ throughout the entire process, without the need for extreme thermal control measures.

[0104] Conclusion: Simulation data fully demonstrate that this disclosure, through systematic collaborative design, transforms an unstable thermal environment into a stable one, fundamentally solving the problems of high energy consumption, system complexity, and reliability of traditional solutions, and significantly improving all thermal performance indicators.

[0105] Based on the above method, this disclosure also provides a thermal control design system for high-inclination, high-power communication satellites in medium-high orbits, corresponding to the above method. The system includes... The model building module is used to obtain the precise parameters of the target satellite's target orbit, and to build an external heat flow calculation model based on the precise parameters of the target orbit and the mission lifetime. The attitude definition module is used to calculate the periodic fluctuation amplitude of the external heat flow of each surface in the target satellite body coordinate system based on the external heat flow calculation model, so as to define the target attitude mode for sun orientation based on the fluctuation amplitude analysis results. The strategy planning module is used to determine the device distribution layout strategy and heat dissipation surface planning strategy based on the target posture pattern; The path construction module is used to construct the target heat transfer path from the device to the heat dissipation surface based on the device distribution layout strategy and the heat dissipation surface planning strategy, and to formulate a zoned thermal management strategy.

[0106] Based on the same inventive concept as the above disclosure, this disclosure also provides an electronic device. The electronic device of this disclosure includes at least one processor and at least one memory electrically connected to the processor. The memory is electrically connected to the processor, wherein the memory stores instructions executable by the at least one processor, which, when executed by the at least one processor, enables the at least one processor to perform the method described above.

[0107] It should be noted that the electrical connection between the above-mentioned units does not necessarily mean the connection between lines. The indirect connection method can be applied to the embodiments of this disclosure as long as it achieves the purpose of this disclosure.

[0108] Based on the same inventive concept, this disclosure also provides a computer storage medium storing a computer program, which, when executed by a processor, implements the steps of the above method.

[0109] Although the present disclosure has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present disclosure.

Claims

1. A thermal control design method for a high-inclination medium-altitude high-orbit high-power communication satellite, characterized in that the method comprises the following steps: obtaining target orbit accurate parameters of a target satellite, and establishing an orbit external heat flow calculation model based on the target orbit accurate parameters and a mission life; calculating fluctuation amplitudes of external heat flows of each surface of the target satellite in each attitude mode in a body coordinate system of the target satellite based on the orbit external heat flow calculation model, and defining a target attitude mode of sun pointing according to a calculation result of the fluctuation amplitudes of each attitude and a plurality of preset constraint conditions; determining a device dispersion layout strategy and a heat dissipation surface planning strategy based on the target attitude mode; constructing a target heat transfer path from a device to a heat dissipation surface according to the device dispersion layout strategy and the heat dissipation surface planning strategy, and formulating a partitioned thermal management strategy.

2. The method of claim 1, characterized in that the step of establishing an orbit external heat flow calculation model based on target orbit accurate parameters and a mission life comprises the following steps: extracting an orbit height, an orbit inclination, an orbit period, an ascending node right ascension and a perigee argument corresponding to the target orbit as the target orbit accurate parameters; calculating time-varying external heat flows of each surface of the satellite in a body coordinate system of the satellite during on-orbit operation of the satellite based on the target orbit accurate parameters and the mission life, wherein the time-varying external heat flows are direct solar radiation heat flows.

3. The method of claim 2, characterized in that the step of calculating fluctuation amplitudes of external heat flows of each surface of the target satellite in each attitude mode in a body coordinate system of the target satellite based on the orbit external heat flow calculation model comprises the following steps: determining real-time direct solar radiation heat flows of each surface of each attitude in the body coordinate system of the target satellite based on the orbit external heat flow calculation model; drawing a heat flow variation diagram of each surface of each attitude based on a plurality of the real-time direct solar radiation heat flows, and analyzing the variation diagram to determine a fluctuation amplitude thereof.

4. The method of claim 3, characterized in that the step of defining a target attitude mode of sun pointing according to a calculation result of the fluctuation amplitudes of each attitude and a plurality of preset constraint conditions comprises the following steps: setting a preset task load constraint, an energy constraint and an attitude control constraint; selecting a sun pointing attitude mode with a minimum total fluctuation amplitude of external heat flows in the body coordinate system of the target satellite based on the above-mentioned preset constraint conditions.

5. The method of claim 4, characterized in that the step of determining a device dispersion layout strategy based on the target attitude mode comprises the following steps: comparing real-time working powers of each device with a preset power threshold based on the real-time working powers of each device, and selecting high-power devices based on a comparison result; establishing an overall satellite thermal model using a thermal analysis software, inputting stable external heat flow data in the target attitude mode, and dispersing the high-power devices.

6. The method of claim 5, characterized in that the step of determining a heat dissipation surface planning strategy based on the target attitude mode comprises the following steps: determining a main heat dissipation candidate surface, an auxiliary heat dissipation surface and a non-heat dissipation surface based on the target attitude mode; applying a high-stability heat dissipation coating to all or a major area outside the main heat dissipation candidate surface; applying a high-emissivity white paint coating to outside of the auxiliary heat dissipation surface; coating the non-heat dissipation surface with a plurality of thermal insulation components. ​ ​ ​ ​ ​ ​ 7. The method of claim 6, wherein, a target heat transfer path from the equipment to the heat dissipation surface is constructed according to the equipment dispersion layout strategy and the heat dissipation surface planning strategy, specifically including: for the in-cabin equipment, a primary heat transfer path is constructed by covering the cabin deck with the orthogonalized stacking pre-embedded heat pipe network; for the out-cabin equipment, a secondary heat transfer path is constructed by using the externally attached heat pipe to conduct heat to the main heat dissipation candidate surface.

8. The method of claim 7, wherein, a partitioned thermal management strategy is formulated, specifically including: the cabin is divided into several independent thermal zones according to the thermal characteristics of the equipment; a corresponding temperature threshold value is set for each independent thermal zone; a thin film type electric heater and a thermistor are arranged in each independent thermal zone, and the temperature threshold value is designed to be passed based on the temperature index and thermal inertia requirement of each independent thermal zone to determine the partitioned thermal management strategy.

9. The method of claim 8, wherein, the temperature threshold value is designed to be passed based on the temperature index and thermal inertia requirement of each independent thermal zone, specifically including: the thermal load characteristics and temperature variation law of any of the independent thermal zones are analyzed, and PID control parameters are set based on the thermal load characteristics and temperature variation law; a temperature control threshold value is set, and when the temperature of the independent thermal zone is lower than the corresponding temperature threshold value, a heating instruction is outputted to start the thin film type electric heater of the zone.

10. A thermal control design system for a large-inclination medium-high orbit large-power consumption communication satellite, wherein, the system includes, a model establishment module configured to obtain target orbit accurate parameters of a target satellite, and establish an orbit external heat flow calculation model based on the target orbit accurate parameters and a mission life; an attitude definition module configured to calculate surface external heat flow fluctuation amplitudes in each attitude mode under a body coordinate system of the target satellite based on the orbit external heat flow calculation model, and define a target attitude mode of sun orientation according to calculation results of each attitude fluctuation amplitude and a plurality of preset constraint conditions; a strategy planning module configured to determine an equipment dispersion layout strategy and a heat dissipation surface planning strategy based on the target attitude mode; a path construction module configured to construct a target heat transfer path from the equipment to the heat dissipation surface according to the equipment dispersion layout strategy and the heat dissipation surface planning strategy, and formulate a partitioned thermal management strategy.

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