A satellite autonomous temperature control and heating system based on orbit information

Abstract

The present invention discloses a satellite autonomous temperature control and heating system based on orbital information, which belongs to the field of satellite thermal control technology. The system includes a heating execution unit, a local control unit, a storage unit and an initial state interface. The storage unit pre-stores satellite orbital information and associated heating strategies. After receiving the initial state information, the local control unit obtains the corresponding heating strategy from the storage unit according to the current time and orbital information, and autonomously controls the operation of the heating execution unit without the need for real-time temperature sensor feedback throughout the process. The present invention also discloses a corresponding control method. The system and method eliminate the need for temperature sensors and related circuits, simplify the system structure, reduce the occupancy of the onboard main controller resources, achieve lightweight, low power consumption and high autonomy, and are particularly suitable for microsatellites. The heating unit and control unit can be integrated on a flexible substrate, which improves integration and spatial adaptability.

Description

Technical Field

[0001] The present invention relates to the field of satellite technology, in particular to a satellite thermal control technology, and more particularly to a satellite autonomous temperature control and heating system based on orbital information. Background Art

[0002] During satellite in-orbit operation, precise thermal control systems are required to ensure that internal equipment operates within an appropriate temperature range. Currently, satellite thermal control technologies are categorized into two main categories: passive and active. Passive thermal control utilizes specialized materials and structural designs to achieve temperature regulation without the need for external energy input, and is typically used as a supplementary measure. Active thermal control, on the other hand, relies on external energy input or dynamic adjustment mechanisms to achieve more precise temperature control. Common technologies include electric heating and cooling systems, fluid circuits and phase change energy storage, loop heat pipes, and radiators.

[0003] In active thermal control, electric heaters are a common method. Traditional electric heating control methods usually include the following steps:

[0004] Temperature acquisition: Use a thermistor (such as PT100, PT1000, MF51, MF501, and MF61) or other temperature sensor to monitor the temperature of the controlled object in real time. Temperature changes cause changes in the sensor resistance or other electrical signal parameters.

[0005] Signal processing and transmission: After being processed, the sensor signal is transmitted via wires to the satellite's on-board controller (OBC) or dedicated thermal control unit.

[0006] Control decision: The onboard controller receives temperature data, compares it with the preset target temperature, and calculates the required heating power through control algorithms such as PID (proportional-integral-differential).

[0007] Heating: The onboard controller sends commands to the electric heater to adjust its heating power. Ground remote control is sometimes used as an auxiliary control method.

[0008] The commonly used structure of spacecraft thin-film electric heaters is usually: two layers of polyimide film, the middle layer is an electric heating metal line formed by processes such as metal foil etching, and the wires are welded to the metal lines for power supply and connection.

[0009] However, for microsatellites (Nanosatellites), which have extremely limited size, weight, power consumption, and computing resources, the above traditional active thermal control methods have significant disadvantages:

[0010] (1) High system complexity: It requires temperature sensors, signal conditioning circuits, connecting wires, and complex control logic in the onboard controller, which increases the complexity of system design, integration, and testing.

[0011] (2) Occupies many resources: Temperature sensors and a large number of wires increase the size and weight of the system; real-time temperature acquisition and the operation of algorithms such as PID occupy valuable computing resources (computing power) and power consumption of the onboard controller.

[0012] (3) Poor adaptability and portability: Complex wiring and discrete components are not conducive to flexible deployment in the extremely compact space of microsatellites.

[0013] Therefore, there is an urgent need for a new heating control technology that is simpler, lighter, lower power and suitable for microsatellites. Summary of the Invention

[0014] The present invention aims to overcome the shortcomings of the existing technology and provide an autonomous temperature control and heating system and its control method that are simple in structure, lightweight, low in power consumption, simple in control circuit, do not require real-time temperature sensor feedback, do not rely on or reduce the reliance on the computing power of the onboard main controller, and are particularly suitable for microsatellites.

[0015] To solve the above technical problems, the present invention provides a satellite autonomous temperature control and heating system based on orbital information, comprising:

[0016] Heating execution unit: used to generate heat to heat satellite components;

[0017] Local control unit: integrated with or tightly coupled to the heating execution unit, used to control the working state of the heating execution unit according to preset logic;

[0018] Storage unit: connected to the local control unit, pre-stored with satellite orbit information and heating strategy data associated with the orbit information;

[0019] Initial state interface: used to receive the initial state information of the satellite (for example, initial position, time, attitude, etc.).

[0020] It is characterized in that the local control unit is configured to:

[0021] Receiving initial state information of the satellite through the initial state interface;

[0022] Based on the received initial state information and the current time (or the time inferred from the initial state), querying or calculating the preset heating strategy data corresponding to the current orbital position or stage from the storage unit;

[0023] autonomously determining a target heating power or operating mode of the heating execution unit according to the preset heating strategy data;

[0024] The heating execution unit is controlled to operate according to the determined target heating power or working mode to achieve temperature regulation.

[0025] Crucially, when the local control unit executes the above-mentioned heating control process, it does not need to receive feedback signals from external real-time temperature sensors, and can run its core control logic independently of the satellite's main onboard controller.

[0026] In a preferred embodiment, the heating execution unit and the local control unit (including necessary circuits thereof) are formed on a flexible substrate through an integrated manufacturing process (eg, flexible circuit board etching) to form an integrated flexible heating control module.

[0027] In a preferred embodiment, the orbit information stored in the storage unit includes time-varying data or model parameters of the satellite's position, velocity, attitude, lighting conditions (entering / leaving shadow areas), etc. within one or more orbital periods.

[0028] In a preferred embodiment, the heating strategy data stored in the storage unit includes control parameters such as preset heating power levels, heating on / off times, or duty cycles corresponding to different orbital positions, orbital phases, or illumination conditions. This strategy data is derived through pre-calculated ground-based simulations based on the satellite thermal model, expected external heat flux variations, and target temperature requirements.

[0029] In a preferred embodiment, the local control unit comprises a microcontroller (MCU) or an application specific integrated circuit (ASIC) for executing control logic and data query / calculation.

[0030] In a preferred embodiment, the initial state interface can receive initial state information once or a limited number of times from an onboard main controller or other designated source via a wired or wireless manner after satellite deployment or at a specific time point.

[0031] The present invention also provides a satellite autonomous temperature control and heating control method based on orbital information, which is applied to the above system. The method includes the following steps:

[0032] a) Initialization: At a predetermined time or under certain conditions, the initial state information of the satellite (such as initial position, time, etc.) is received through the initial state interface;

[0033] b) State determination: The local control unit determines the satellite’s current orbital position or orbital phase based on the received initial state information and the internal clock (or time calculation);

[0034] c) Strategy query / calculation: The local control unit accesses the storage unit and queries or calculates the corresponding preset heating strategy data (such as target heating power, start and stop instructions, etc.) based on the current orbital position or stage;

[0035] d) Heating control: The local control unit autonomously generates control signals based on the acquired heating strategy data, driving the heating execution unit to operate according to the specified strategy;

[0036] e) Loop / Update: As time goes by, the local control unit periodically repeats steps b) to d) to dynamically adjust the heating strategy based on the satellite's operation in orbit.

[0037] Crucially, steps c) and d) of the method are performed independently of real-time temperature measurement feedback.

[0038] Compared with the prior art, the present invention has the following significant beneficial effects:

[0039] Simplify the system and reduce complexity: No temperature sensor and its related signal conditioning and transmission lines are required, which greatly simplifies the hardware structure and circuit complexity of the thermal control system.

[0040] Save resources and achieve lightweight: Eliminating sensors and some cables helps to achieve lightweight satellite systems; the heating actuator unit and local control circuit are integrated into one manufacturing unit (such as flexible etching), which has a compact structure and saves space, making it particularly suitable for microsatellites where space is extremely valuable.

[0041] Reduced power consumption and computational burden: Control logic is executed in the local control unit, eliminating or significantly reducing the computing power required by the satellite's main onboard controller. This reduces the main controller's power consumption and computational load, improving its efficiency in handling other critical tasks. The local control unit itself can also be designed for low-power operation.

[0042] Improved autonomy and efficiency: Feedforward control based on pre-calculated trajectory information enables autonomous operation of the heater, reducing reliance on ground commands or complex closed-loop control, and improving the real-time control response (compared to centralized control relying on a master controller).

[0043] Optimize production process: The heater part and the flexible control circuit are integrated into an etched shape, which simplifies the production and assembly process and shortens the production cycle.

[0044] Enhanced adaptability: The integrated design with a flexible substrate makes it easier to install in small or irregular spaces inside satellites. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] Figure 1 This is the overall system block diagram.

[0046] Figure 2 This is a flow chart of satellite orbit calculation. DETAILED DESCRIPTION

[0047] To make the purpose, technical solutions and advantages of the present invention clearer, the present invention will be described in detail below with reference to specific embodiments. It should be noted that, unless there is a conflict, the embodiments and features in the embodiments of the present application can be combined with each other.

[0048] Example 1: Integrated heating control module based on flexible circuit board

[0049] This embodiment provides an integrated autonomous temperature-controlled heating module, which is entirely fabricated on a flexible polyimide (PI) substrate.

[0050] Heating execution unit: On one or more layers of the PI substrate, electric heating lines of predetermined shape and resistance value are formed through a metal foil (such as Constantan, nickel-chromium alloy) etching process.

[0051] Local control unit: On another area or layer of the same PI substrate, a low-power microcontroller (MCU) chip, non-volatile memory chip (such as Flash Memory), and necessary power management and interface circuits are integrated. The MCU, memory, and peripheral components can be fixed to the flexible substrate using SMT (surface mount technology) or other microassembly technologies.

[0052] Storage unit: This is the aforementioned non-volatile memory chip. Before launch or during the initial phase of the satellite's orbit, calculated orbital data and the corresponding heating power table (LUT) or heating control algorithm parameters are written to this memory via a specific interface. Orbital data may include key milestones for the next several days or orbital cycles (such as shadow entry / exit times, specific latitude / longitude transit times, etc.), as well as corresponding external heat flux predictions. The heating power table defines the power output to the heating wires by the MCU (e.g., through PWM duty cycle control) for different orbital segments or conditions.

[0053] Initial state interface: This can be a simple serial communication interface (such as UART, SPI, or I2C) or a few specific GPIO pins. After the satellite separates from the launch vehicle or receives the first ground command, the onboard main controller can use this interface to send initial state information such as the current precise time, orbital six-element numbers (or other forms of position / velocity vectors) to the module.

[0054] Integrated manufacturing: The wiring of the heating lines and control circuits is formed in one step on the flexible PI substrate through an etching process, achieving a high degree of integration of heating and control functions.

[0055] Workflow:

[0056] After the module is powered on, the MCU enters the standby state.

[0057] After receiving the initial status information through the initial status interface, the MCU stores it and starts a timer internally or uses the internal real-time clock (if any).

[0058] Based on the current time and initial orbit information, the MCU calculates the satellite's current position in orbit or the phase it is in (for example, whether it is in the sunlit or shadowed area, how long it will take until it enters / leaves the shadowed area next time, etc.).

[0059] The MCU uses this track position / stage information as an index to search the storage unit for the corresponding preset heating power value or start / stop instruction.

[0060] The MCU controls the drive circuit (such as MOSFET switch) to apply voltage to the heating wire using PWM or other methods to generate the queried target power.

[0061] The MCU continuously updates its prediction of the satellite's orbital position / phase over time and periodically queries and adjusts the heating power, enabling open-loop temperature control based on orbital predictions. This entire process eliminates the need for real-time data from external temperature sensors.

[0062] Example 2: Control method

[0063] This embodiment describes the control method executed by the MCU in Example 1:

[0064] Initialization phase: The MCU waits to receive data through the initial state interface. Once a valid initial time T0 and initial orbit parameter P0 are received, the information is recorded and the internal timer is started (or the internal clock is synchronized).

[0065] Orbital Position / Phase Determination: The MCU internally runs a simplified orbital dynamics model or table lookup routine. Based on T0, P0, and the current time T_current (obtained from an internal timer), it calculates or looks up the current orbital state S_current (e.g., whether it is in the shadow zone, the estimated remaining shadow zone time, the current latitude range, etc.).

[0066] Heating strategy query: The MCU uses S_current as an index to search for the corresponding heating power setting value Power_target or control mode Mode_target (e.g., full power heating, half power heating, heating off, heating with a specific duty cycle, etc.) in a pre-stored heating strategy database (which can be a lookup table or a set of rules). This database is generated in advance based on detailed thermal analysis and track simulation.

[0067] Heating execution: The MCU controls its output port (such as PWM output pin) to generate a corresponding drive signal according to Power_target or Mode_target, and applies it to the heating execution unit through the power switching circuit.

[0068] Periodic Updates: The MCU repeats steps 2 to 4 at a preset time step (e.g., every tens of seconds or minutes), continuously adjusting the heating output based on the satellite’s progress in orbit.

[0069] Key advantages:

[0070] Sensorless: This method does not rely on any real-time temperature feedback.

[0071] Autonomy: Once initialized, the MCU operates independently without the need for constant intervention from the onboard host controller. The host controller only needs to communicate with the module when it needs to update the orbit model or strategy (if the design supports on-orbit updates).

[0072] The amount of computation required is controllable: The amount of computation required for track position determination and table lookup operations is much smaller than that required for real-time PID control and sensor data processing. Therefore, the MCU can be selected with low power consumption and low cost.

[0073] Other considerations:

[0074] Robustness: Multiple orbit models or heating strategies can be backed up in the storage unit to cope with orbital perturbations or initial state errors. Simple fault detection logic can also be designed, such as detecting abnormal heater current.

[0075] Hybrid mode: In some demanding applications, the system of the present invention can be used as a basic heating system, supplemented by a simple, threshold-triggered high / low temperature protection sensor and logic, but without precise PID adjustment, thus still maintaining the advantages of system complexity.

[0076] Communication method: Although cable-free is preferred, when high interference resistance is required, initial status information and possible strategy updates can also be transmitted via well-shielded cables.

[0077] In summary, this embodiment, through a combination of hardware and software, leverages pre-calculated orbital information and a corresponding heating strategy to achieve autonomous temperature control for satellite heaters, eliminating the need for real-time temperature sensors and complex PID calculations in an onboard controller. This approach is particularly suitable for microsatellite platforms with strict weight, power consumption, volume, and cost constraints, and offers significant practical value and innovation.

[0078] Example 3: Control strategy based on parameterized track model and thermal model

[0079] Different from the first embodiment in which a lookup table (LUT) is used to store the heating strategy, the storage unit of this embodiment stores the correlation coefficients and boundary conditions of the parameterized model.

[0080] Storage contents:

[0081] (1) Simplified orbit model parameters: For example, the parameter set required to calculate the satellite position, velocity, and determine the illuminated / shadowed area of the simplified orbit propagation model (such as a simplified version of the SGP4 model or a periodic function fitting for a specific orbit type). These parameters can be obtained by ground-based fitting based on the precise ephemeris.

[0082] (2) Simplified thermal model parameters: stores key parameters of a simplified thermal model (e.g., a first-order or second-order thermal network model) that describes the thermal characteristics of the heated component, such as heat capacity, thermal conductivity, radiation / absorption coefficient to the external environment, etc.

[0083] (3) Control law parameters: Stores the control law parameters used to calculate the heating power based on the predicted temperature and the target temperature (a simplified feedforward control law or a correction rule based on the predicted deviation, but not a real-time temperature feedback PID).

[0084] Local Control Unit (MCU) tasks:

[0085] 1. Receive initial state information (T0, P0).

[0086] 2. Using the stored orbital model parameters and the current time T_current, the current orbital position, attitude, and external heat flow conditions (solar radiation, earth reflection / infrared radiation, etc.) are calculated in real time.

[0087] 3. Using the calculated external heat flux as input and the stored thermal model parameters, predict the temperature change trend T_predicted of the controlled component if no heating is performed or heating is performed at a certain base power within a specific time period (e.g., the next few minutes or a control cycle).

[0088] 4. Compare the predicted temperature T_predicted with the locally stored target temperature range T_target (which may also vary with the orbit).

[0089] 5. Based on the comparison results and the stored control law parameters, the heating power Power_calculated that needs to be applied is calculated so that the future temperature is kept within the T_target range as much as possible.

[0090] 6. Control the heating execution unit to output Power_calculated.

[0091] 7. Repeat steps 2-6 periodically.

[0092] Advantages: Compared to LUTs, this approach may require less storage space (storing parameters rather than a large number of data points) and is theoretically more adaptable to small changes in the track or environment (calculated by the model rather than by table lookup).

[0093] Challenges: The MCU needs to have a certain amount of computing power to perform model calculations; the simplicity and accuracy of the model need to be carefully balanced.

[0094] Example 4: Structural parts of two working modes

[0095] After the satellite is launched, it enters the corresponding orbit. The satellite needs to pass through two working conditions in the orbit: the sunlit area and the shadowed area. The heating power required in these two working conditions and the power conditions when they change alternately are different.

[0096] The electric heating plate in the thin-film electric heater is composed of lead wires, electric heating metal lines (metal foil etching), and two layers of polyimide film. During its production process, it needs to go through the processes of design, photo-drawing, exposure, plate making, etc. In the design stage. FPCB (flexible circuit board) is a circuit board composed of an insulating substrate and a conductive layer. During the design, the conductive layer of the FPCB (flexible circuit board) and the heating metal wire of the heating circuit are designed on the same film at the same time, and etching work is carried out at the same time. The welding holes for the relevant patch welding are punched on the upper insulating film, and the corresponding welding holes are aligned with the designed solder points. After being integrated with the heating circuit, the corresponding components are patch welded to achieve lightweight integration of the heater and the control system. The overall system block diagram is as follows Figure 1 shown.

[0097] The corresponding orbital information and embedded program are input into the main control MCU (microcontroller chip) of the welded FPCB (flexible printed circuit board). During operation, after the power input (powered by the satellite) enters the power management module, which distributes the required current and voltage to each component. The onboard controller inputs the initial orbital information to the main control MCU (microcontroller chip) through the communication interface (using a Bluetooth module). The main control MCU's algorithm calculates the PWM signal (pulse width modulation wave) of the output pin. The high and low voltage of the output pulse signal controls the on and off of the electronic switch (MOS transistor), starting and stopping the heating circuit to achieve temperature control.

[0098] Example 5: Working principles of two working modes

[0099] This embodiment describes in detail the working principle of the satellite autonomous temperature control heating system under two typical working modes (sunlit area and shadowed area). Its core lies in accurately calculating the satellite orbital position through the embedded programming module and adjusting the heating power accordingly. Figure 2The satellite orbit calculation flow chart shown in the figure mainly relies on accurate orbital dynamics models and numerical integration methods:

[0100] 1. Self-controlled heating plate

[0101] The main control MCU (microcontroller chip) communicates with the onboard controller through the communication interface (CAN Bluetooth module) to obtain the initial information such as the current satellite position, time, attitude, etc. This process corresponds to Figure 2 The embedded programming module will then execute the initial orbit parameter input phase. Figure 2 The complex calculation process shown in the figure predicts the satellite's future trajectory, attitude, time, and spatial nodes by numerically integrating the satellite's equations of motion. Based on the trajectory, time, and spatial nodes, the system determines the environmental conditions (sunlit or shaded) and calculates the required compensation power in real time based on these conditions. The main control MCU (microcontroller) outputs control signals to the electronic switches (MOSFETs), enabling the heating circuit to start and stop, adjust the heating power, and achieve autonomous temperature control.

[0102] When the satellite is in the sun, the heating power is low; when it is in the shadow, the heating power is high. According to the algorithm, different heating powers are provided according to different orbital positions, achieving the purpose of adaptive heating function.

[0103] 2. Embedded programming module

[0104] Embedded programming is a program written for the embedded system on the heating chip, the purpose of which is to calculate the orbital position of the satellite in space, and is written in C language or assembly language. This module is responsible for implementing Figure 2 The orbit prediction algorithm shown in the figure analyzes the spatial relationship between the satellite and the Earth and outputs state variables, thereby controlling the heating power of the heater and achieving automatic control. The advantages of targeting specific hardware include high integration, low power consumption, and real-time processing.

[0105] In satellite orbit prediction, the input parameters are the initial orbit parameters of the satellite. This system uses the universal double row element number TLE as the initial condition. After obtaining the initial orbit parameters, refer to Figure 2 The embedded module performs precise orbit prediction calculations. This calculation first requires accurate time and coordinate system conversion, which involves calculating Greenwich Mean Sidereal Time (GMST), precession, nutation, and polar motion to determine the transformation matrix W from the Earth-centered inertial system to the Earth-centered fixed system or other desired coordinate system.

[0106] At the same time, if Figure 2As shown, it is necessary to calculate the precise positions of the sun and moon (to find the positions of the sun and moon) because they are the main sources of gravitational perturbations and solar pressure perturbations. Based on the current state of the satellite (position, velocity), the positions of the sun and moon, and the coordinate transformation relationship, it is necessary to calculate the accelerations generated by the various forces acting on the satellite. is the initial acceleration vector, is the Earth's gravitational acceleration vector, is the solar radiation acceleration vector. GMST calculations are key time parameters for calculating Greenwich Mean Time (GMT) and transforming astronomical coordinate systems. Precession calculations calculate the slow precession (drift) of the Earth's rotation axis due to long-term gravitational forces, used to correct coordinate systems. Nutation calculations calculate the short-term periodic wobble of the Earth's rotation axis due to factors such as the gravitational pull of the sun and moon, used to correct coordinate systems. Polar motion calculations calculate the tiny movement of the Earth's rotation pole relative to the Earth's crust, used to accurately transform the Earth-centered fixed coordinate system. The coordinate transformation matrix W is calculated based on the results of GMST, precession, nutation, and polar motion, used to transform between different astronomical coordinate systems. Sol-lunar position calculations calculate the precise position vectors of the Sun and Moon at a specific moment in a reference coordinate system (usually the Earth-centered inertial system). This serves as the basis for calculating gravitational perturbations and solar radiation pressure perturbations. The Runge-Kutta method uses the Runge-Kutta numerical integration method to provide the state vectors (position and velocity) at several consecutive time points required for the start of subsequent multi-step integration methods (such as Adams-Cowell). Adams-Cowell integration uses the Adams-Cowell linear multi-step numerical integration method to integrate the satellite's differential equation of motion based on the calculated total acceleration to predict the future orbital state. Orbital prediction refers to the position and velocity sequence of the satellite over a period of time in the future obtained using this integration method.

[0107] Two-Line Element Set (TLE) is a standardized data format for describing satellite orbital parameters. It is widely used in satellite orbit prediction and tracking. TLE consists of two lines of 69 characters each, containing the satellite's orbital information, as defined below:

[0108] First line:

[0109] Line number: The first character, usually "1".

[0110] Satellite number: Characters 3-7, NORAD number.

[0111] Classification: 8th character, usually "U" (unclassified).

[0112] International number: characters 10-17, the year and number of launch.

[0113] Epoch time: Characters 19-32 represent the UTC time corresponding to the data.

[0114] First derivative of the mean motion: characters 34-43, rate of change of orbit.

[0115] Second derivatives of mean motion: characters 45-52, orbital variation acceleration.

[0116] BSTAR drag coefficient: Characters 54-61, influence of atmospheric drag.

[0117] Track model: 63rd character, usually "0".

[0118] Element set number: characters 65-68, TLE release number.

[0119] Checksum: The 69th character is used to verify data integrity.

[0120] Second row

[0121] Line number: The first character, usually "2".

[0122] Satellite number: Characters 3-7, NORAD number.

[0123] Orbital inclination: Characters 9-16, the angle between the orbital plane and the equatorial plane.

[0124] Ascending node right ascension: Characters 18-25, the angle between the ascending node and the vernal equinox.

[0125] Eccentricity: Characters 27-33, elliptical shape of the orbit.

[0126] Argument of perigee: Characters 35-42, the angle between perigee and ascending node.

[0127] Mean anomaly: Characters 44-51, the position of the satellite in orbit.

[0128] Average motion: Characters 53-63, the number of times the satellite orbits the Earth per day.

[0129] Number of orbits: Characters 64-68, the total number of orbits since launch.

[0130] Checksum: The 69th character is used to verify data integrity.

[0131] in accordance with Figure 2As shown in the process, after obtaining the initial orbit parameters, the orbit extrapolation and solution phase begins. The numerical integration method is used to simulate the change of the orbit over time. The satellite motion equation is numerically integrated with a set of correct initial values to extrapolate the future satellite orbit. In the case of a relatively complete satellite motion force model, the accuracy of the initial value will directly affect the accuracy of the extrapolated orbit. During the extrapolation process, due to the influence of the initial value error, the longer the extrapolation interval, the greater the error of the integral accumulation. The orbit calculation steps are as follows: Figure 2 shown.

[0132] In actual positioning calculation, in order to obtain the precise ephemeris coordinates at a specific moment, interpolation processing may be required. Figure 2 For example, we need precise ephemeris coordinates with an interval of 1 second or even smaller step size. Based on the accuracy and low computational cost, we use the Newton polynomial interpolation method of data mean difference, assuming that control points , defined in The zero-order mean difference at ,exist The first-order mean difference at is defined as , the k-order mean difference is defined as:

[0133]

[0134] Then the Newton interpolation polynomial can be expressed as:

[0135]

[0136] Each level consists of 2 additions and 1 multiplication operations, and the time consumption is: Compared with the classical Lagrange polynomial interpolation, Newton polynomial interpolation is much more efficient. Given Different points and the corresponding mean difference coefficient , for any moment The interpolation polynomial is generated by the following iteration (Horner's algorithm). Here, n represents the number of known control points. A is the result of addition. M is the result of multiplication. k is the order of the mean difference.

[0137]

[0138] The accuracy and time consumption of the above algorithm are within an acceptable range, and the mean differences of each order can be pre-calculated and stored, and can be directly called when needed.

[0139] Satellite orbit data is predicted by double row elements. Figure 2In the process, after orbit calculation, the state judgment and output phase begins. When the actual satellite mission is executed, the satellite position can be obtained in real time by injecting the mission start time. According to the relationship between the sun and the earth and the satellite position, it can be output whether the satellite is in the sunlit area (output value 1) or the shadow area (output value 0), as well as the remaining time in the area. These output information will be used as Figure 2 The final result of the process is used to guide the main control MCU (microcontroller chip) of the integrated heater to achieve the heating power change of the electric heater. To reduce the control error, the main control MCU (microcontroller chip) performs position calibration with the onboard controller after a certain period of operation. This corresponds to Figure 2 The process may include track calibration and correction steps to ensure long-term operation accuracy.

[0140] Example 6: Distributed multi-zone autonomous heating system

[0141] For satellite components with complex structures or widely varying thermal requirements, multiple autonomous temperature-controlled heating modules of the present invention may be used to form a distributed system.

[0142] System composition: N independent autonomous temperature-controlled heating modules are deployed on the satellite (each module has a structure similar to that of Example 1 or 3). Each module is responsible for heating a specific area or component.

[0143] Data Storage: Each module's memory cell stores heating strategies influenced by orbital information related to its area of responsibility. For example, the lighting conditions for devices on either side of the satellite are different at the same orbital location, so the heating strategies stored in the modules on both sides will also be different.

[0144] Initialization: All modules can share the same initial state interface or receive initial state information separately. It is necessary to ensure that their time bases are synchronized.

[0145] Coordination (optional):

[0146] No coordination: Each module works completely independently.

[0147] Simple coordination: Modules can exchange very limited information via a simple bus (such as CAN or RS485). This can include broadcasting time synchronization signals or notifying other modules to enter safe mode when a module detects a global anomaly (such as a power supply undervoltage). However, this avoids complex real-time temperature information sharing and centralized control.

[0148] Advantages: Good scalability, allowing for refined partition management of large or complex thermal structures while maintaining the simplicity and autonomy of individual modules. Good fault isolation, meaning failure of one module does not affect the operation of other modules.

[0149] Challenge: It is necessary to manage the generation and loading of policies for multiple modules; if coordination is required, it will increase communication overhead and complexity.

[0150] The foregoing description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art will readily appreciate that various modifications and variations of the present invention are possible. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention are intended to be included within the scope of protection of the present invention.

Claims

1. A satellite autonomous temperature control and heating system based on orbital information, characterized in that: include: A heating execution unit, used for heating satellite components; a local control unit coupled to the heating execution unit; a storage unit connected to the local control unit, pre-stored with satellite orbit information and heating strategy data associated with the orbit information; An initial state interface is used to receive the initial state information of the satellite; wherein the local control unit is configured to: based on the received initial state information and internal time information, obtain the heating strategy data corresponding to the current orbital state from the storage unit, and autonomously determine and control the working state of the heating execution unit according to the heating strategy data to achieve temperature regulation; and, in the process of executing heating control, the local control unit does not rely on the feedback signal from the external real-time temperature sensor, the orbital information stored in the storage unit includes data or model parameters of the satellite's position, speed, attitude or lighting conditions changing over time in one or more orbital periods, and the heating strategy data stored in the storage unit includes preset heating power levels, heating start and stop times or duty cycle parameters corresponding to different orbital positions, orbital stages or lighting conditions.

2. The system according to claim 1, wherein: The heating execution unit and the local control unit are integrated and manufactured on the same flexible substrate.

3. The system according to claim 2, characterized in that The heating execution unit and the related circuits of the local control unit are formed by performing an etching process on the flexible substrate.

4. The system according to claim 1, wherein: The heating strategy data is obtained through ground pre-simulation calculation based on the satellite thermal model, expected external heat flux changes and target temperature requirements.

5. The system according to claim 1, wherein: The local control unit includes a microcontroller (MCU) or an application-specific integrated circuit (ASIC).

6. The system according to claim 1, wherein: The initial state information includes the initial position, initial time, initial velocity or orbital element number of the satellite.

7. A satellite autonomous temperature control and heating control method based on orbital information, applied to the system according to any one of claims 1 to 6, characterized in that: The method comprises the following steps: a) enabling the local control unit to receive initial state information of the satellite through the initial state interface; b) the local control unit determines the current orbital state of the satellite based on the received initial state information and internal time information; c) the local control unit accesses the storage unit and queries or calculates corresponding preset heating strategy data according to the current track state; d) the local control unit autonomously generates a control signal based on the acquired heating strategy data to drive the heating execution unit to operate according to the specified strategy; The execution of steps c) and d) does not depend on real-time temperature measurement value feedback.

8. The method according to claim 7, characterized in that Steps b) to d) are periodically repeated to dynamically adjust the heating strategy according to the operation of the satellite in orbit.

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