Satellite infrared camera on-orbit autonomous imaging control method, storage medium and equipment

Abstract

The present application relates to the technical field of satellite payload control, and particularly relates to a satellite infrared camera on-orbit autonomous imaging control method, a storage medium and equipment, comprising: S1: adopting Kalman filtering to fuse GPS measured data and satellite-borne orbit prediction data, and performing spatial and time double confirmation according to a preset entry and exit criterion, and recording as a base time point when the latitude and longitude boundary conditions are met in a continuous set time window; S2: sending power-on instructions in time based on the base time point, staggered execution of medium and long wave and short wave infrared load startup and parameter configuration, after completing the window configuration, controlling the two loads to enter the imaging mode synchronously and starting the fixed storage record; S3: after flying away from the airspace of the country, sequentially powering off according to the shutdown time sequence to restore the initial state, calculating the total time length of the whole process and modifying the time sequence parameters through the number of notes, and ensuring that the total time length is strictly less than the current orbit period. The present application realizes autonomous imaging of the whole process without human intervention, and has high reliability, low power consumption and orbit period adaptive capacity.

Description

Technical Field

[0001] This invention relates to the field of satellite payload control technology, and in particular to a method, storage medium, and device for on-orbit autonomous imaging control of a satellite infrared camera. Background Technology

[0002] With the rapid development of space remote sensing technology, satellite payload control systems are showing a significant trend towards autonomy and intelligence. Against this backdrop, to improve the reliability and mission response efficiency of satellite infrared cameras in orbit, traditional technologies typically employ designs that use real-time ground command control or fixed program control. These mainly encompass ground station uplink remote control, on-board fixed timing triggering, and single-condition triggering based on simple latitude and longitude criteria.

[0003] During operation, the satellite's infrared camera relies entirely on real-time commands within the ground control arc to perform power-on, imaging, and power-off actions. When the satellite passes over the target area, if this arc does not coincide with the ground station's visible arc, ground commands cannot be received. Delayed commands must be pre-loaded according to mission planning, which limits the system's real-time response capability to dynamic factors such as orbital perturbations and attitude deviations. Furthermore, if the satellite-to-ground link is interrupted or command uploading fails, the imaging mission will be lost.

[0004] Onboard fixed-time triggering technology is based on a preset timetable for action scheduling. The satellite performs payload power-on and power-off at specific orbital positions according to the pre-determined time sequence. However, because the orbital altitude of low-Earth orbit satellites decays over time and the orbital period continuously shortens, a cumulative drift occurs between the fixed timetable and the actual ground track. This causes the preset triggering time to gradually deviate from the target area, making it impossible to maintain mission accuracy in the long term. In addition, this technology lacks the ability to autonomously adjust according to changes in on-orbit operating conditions, resulting in poor flexibility.

[0005] While single-condition triggering technology based on simple latitude and longitude criteria achieves closed-loop position control, its criterion logic relies solely on real-time positioning and single-point sampling. Under abnormal conditions such as GPS signal loss, instantaneous changes in positioning data, or sudden increases in orbital recursion errors, it is highly susceptible to false triggering or missed triggering. This can cause infrared cameras to be ineffectively activated in non-target areas, wasting valuable primary energy and on-orbit storage resources, and even damaging the payload's lifespan due to repeated false power-on and power-off.

[0006] In practical applications, the reliability and environmental adaptability requirements of various operating parameters of infrared cameras differ significantly. The temperature control settling time for mid- and long-wave infrared payloads, the TEC cooling stabilization time for short-wave infrared payloads, and the peak power distribution characteristics of their coordinated imaging all vary. While key parameters such as target temperature, integration time, and gain settings are few in number, they have a significant impact on image quality; whereas most timing interval parameters and ordinary operating condition parameters have relatively lower accuracy requirements. However, traditional satellite payload control schemes are difficult to change once the architecture is determined, with all parameters using a unified upload update and activation mechanism. This forces the control system to reserve overall resources and allocate energy according to the most stringent imaging quality requirements, maintaining a high-power standby state even during non-critical mission phases. This results in excessive energy system design margins for the satellite platform, leading to wasted overall satellite resources and significant shortcomings in terms of economy and practicality.

[0007] Furthermore, none of the aforementioned existing technical solutions effectively address the timing matching challenge between the inability of onboard satellites to accurately calculate the arrival time in advance and the lengthy preparation process of infrared cameras. Infrared cameras require tens of minutes of preheating to reach a stable operating state upon arrival, but the onboard computer, limited by computing power and model accuracy, struggles to autonomously run high-precision orbit recursion to predict the arrival time. Existing methods either rely on ground-based forecasting (resulting in a loss of autonomy) or employ premature startup and idle operation (wasting energy), neither of which can achieve a balance between "precise lead time" and "autonomous position triggering" without human intervention.

[0008] In summary, there is an urgent need for an on-orbit autonomous imaging control method for satellite infrared cameras that can overcome the above-mentioned defects, so as to achieve full-process autonomous imaging of border areas under unattended operation, without real-time ground intervention, and without high-precision satellite orbit recursion, and to have the ability to dynamically reconstruct parameters on orbit and adapt to orbital period decay. Summary of the Invention

[0009] The purpose of this invention is to overcome the shortcomings of existing technologies and provide an on-orbit autonomous imaging control method for satellite infrared cameras, comprising the following steps: S1: Preset the infrared camera power-off status and entry / exit criteria parameters, acquire satellite orbit position information in real time, use Kalman filter to fuse GPS measured data and satellite orbit prediction data, and perform spatial and temporal dual confirmation according to the preset entry / exit criteria. When the preset latitude and longitude boundary conditions are met and the conditions are met within a continuous set time window, it is recorded as the base time point. S2: Taking the base time point as a reference, send power-on commands at different preset time intervals in a time-sharing manner, stagger the execution of the startup and parameter configuration sub-processes of the medium-wave infrared payload and the short-wave infrared payload. After completing the image windowing configuration, control the medium-wave infrared payload and the short-wave infrared payload to enter the imaging mode synchronously, and enable the solid-state recording function; S3: After determining that the satellite has flown out over the national border, stop the solid-state recording step by step according to the preset shutdown timing sequence and cut off the power supply of the medium-wave infrared payload and the short-wave infrared payload to restore the power-off state. Calculate the total duration of the entire process from the base time point to the end of power-off, and modify the time interval parameter through ground injection to ensure that the total duration of the entire process is strictly less than the current satellite orbit period.

[0010] Preferably, in step S1, perform double confirmation of space and time according to the preset entry and exit criteria. When the preset latitude and longitude boundary conditions are met and this condition is satisfied within the continuously set time window, record it as the base time point, including: When the satellite descends through the preset southern latitude boundary and the longitude is within the preset first longitude interval, or ascends through the preset northern latitude boundary and the longitude is within the preset second longitude interval, and the preset time window meets the corresponding latitude and longitude conditions, it is determined as a valid trigger and recorded as the base time point; When the GPS measured data is out of lock or the data validity is abnormal, automatically switch to the extrapolation mode mainly based on the on-board orbit prediction data. At this time, the Kalman filter only performs time update and no longer performs measurement update. Combining the preset time window confirmation mechanism, eliminate the influence of single-point noise caused by instantaneous jitter of orbit positioning or GPS out-of-lock anomaly.

[0011] Preferably, in step S2, taking the base time point as a reference, send power-on commands at different preset time intervals in a time-sharing manner, stagger the execution of the startup and parameter configuration sub-processes of the medium-wave infrared payload and the short-wave infrared payload, including: At the base time point + T1, send a power-on command for the medium-wave infrared payload, making the medium-wave infrared payload enter the low-power mode and the shutter always closed. After power-on, send a time calibration command, a temperature control target temperature command, and a heat preservation mode command in sequence; At the base time point + T2, send a power-on command for the short-wave infrared payload, making the short-wave infrared payload enter the low-power mode and the shutter always closed; Where T1 and T2 are the timing interval parameters modified through ground injection, and T1 < T2, to stagger the peak power times of the thermal control establishment and refrigeration start of the two types of payloads.

[0012] Preferably, in step S2, after completing the image windowing configuration, control the medium-wave infrared payload and the short-wave infrared payload to enter the imaging mode synchronously, including: After the shortwave infrared payload is powered on, it sequentially sends a low-power mode power supply start command, a gain setting command, an integration time setting command, an internal trigger frame frequency setting command, a TEC temperature setting command, and a TEC cooling function start command to complete the shortwave infrared payload parameter configuration. After the shortwave infrared payload is started, a medium- and longwave infrared shutter correction command is sent. After the correction is completed, the start line command and output line number command of BAND1 to BAND4 are sent in sequence to realize the windowed acquisition of the image in the specified area. After the windowing configuration is completed, the medium- and long-wave solid-state recording and the short-wave infrared solid-state recording are started sequentially at preset time intervals, and imaging mode commands and imaging function activation commands are sent respectively, so that the medium- and long-wave infrared payload and the short-wave infrared payload enter the imaging state synchronously and in parallel.

[0013] Preferably, in step S3, after determining that the satellite has left the country's airspace, the power supply to the mid- and long-wave infrared payloads and the short-wave infrared payloads is cut off in a preset shutdown sequence to restore the power-off state. First, control the mid-to-long-wave infrared load to enter the heat preservation mode and stop the mid-to-long-wave infrared solid-state recording; The imaging function and TEC cooling function of the shortwave infrared payload are turned off in sequence, the shortwave infrared solid-state recording is stopped, the power supply of the shortwave low-power mode is turned off to put it into standby mode, and the power supply of the shortwave infrared payload is cut off after a delay. After the short-wave infrared payload is powered off, the medium- and long-wave infrared payload is controlled to enter standby mode. After a delay, the power supply to the medium- and long-wave infrared payload is cut off, so that the infrared camera returns to the power-off state and the number of executed autonomous process instructions is cleared to zero.

[0014] Preferably, in step S3, the total duration of the entire process from the base time point to the end of the power outage is calculated, and the time interval parameter is modified by ground-based data collection to ensure that the total duration of the entire process is strictly less than the current satellite orbital period, including: When the satellite orbital period shortens due to orbital altitude decay, causing the original total duration of the entire process to no longer meet the constraint of being less than the current satellite orbital period, the waiting delay parameters in the T1 and T2 timing interval parameters and the shutdown timing are compressed by ground data injection. This ensures that the single autonomous control process is completely completed before the arrival of the next orbital base time point, preventing timing overlap and conflict between adjacent orbital cycles, while ensuring that the effective imaging time over the national border is greater than the preset minimum imaging duration threshold.

[0015] Preferably, modifying the time interval parameter by ground injection count includes: The variable parameter instructions are separated from the main autonomous control process code and stored independently in the dedicated storage space address of the satellite platform. When executing the autonomous process, the variable parameter instructions are read from the dedicated storage space address in real time as needed. When the timing interval parameters and load condition parameters in the dedicated storage space address are modified by ground data, the updated parameters are automatically read and applied the next time the autonomous process is triggered, so as to adapt to the shooting quality adjustment needs caused by device degradation or target characteristic prediction errors.

[0016] Preferably, in step S1, the entry / exit criterion parameters include preset latitude boundary values, preset latitude boundary values, preset first longitude boundary values, preset second longitude boundary values, and preset third longitude boundary values: Wherein, the North latitude boundary value and the South latitude boundary value are used to define the latitude trigger lines of the ascending and descending orbit crossing criteria, respectively, and the first longitude boundary value, the second longitude boundary value and the third longitude boundary value are used to define the longitude range that is allowed to be triggered in the ascending and descending orbit criteria; All the entry and exit criteria parameters can be modified in orbit via ground-based data entry to adapt to the dynamic adjustment requirements of trigger boundary lines for missions at different orbital altitudes or in different border areas.

[0017] Based on the same concept, the present invention also provides a computer-readable storage medium, wherein when the computer-readable instructions are executed by one or more processors, the one or more processors cause the one or more processors to perform the steps of the on-orbit autonomous imaging control method for a satellite infrared camera as described in any one of the embodiments.

[0018] Based on the same concept, the present invention also provides a computer device, including a memory and one or more processors, wherein the memory stores computer code, and when the computer code is executed by the one or more processors, causes the one or more processors to perform the steps of an on-orbit autonomous imaging control method for a satellite infrared camera as described in any one of the embodiments.

[0019] Compared with the prior art, the beneficial effects of the present invention are: (1) This invention acquires orbital position information in real time during satellite operation, uses Kalman filtering to fuse GPS measured data and satellite orbit prediction data, and performs spatial and temporal dual confirmation based on preset entry and exit criteria. When the preset latitude and longitude boundary conditions are met and the conditions are met within a continuous set time window, it is recorded as the base time point. This realizes automatic switching to orbit extrapolation mode in the case of GPS signal loss or abnormal positioning. The continuous time window mechanism eliminates single-point noise interference, ensuring the high reliability and robustness of the base time point criteria. At the same time, by reverse calculation of the entry advance amount at the latitude crossing time, the invention accurately solves the problem of timing matching between the long preparation process of infrared cameras and the entry time without relying on high-precision satellite orbit recursion.

[0020] (2) This invention uses a base time point as a reference and sends power-on commands at different preset time intervals to stagger the execution of the start-up and parameter configuration sub-processes of the medium- and long-wave infrared payload and the short-wave infrared payload. After completing the image windowing configuration, it controls the two payloads to enter the imaging mode synchronously and start solid-state recording. This realizes the time decoupling of the medium- and long-wave infrared payloads in terms of thermal control setup time and cooling start-up characteristics, effectively staggers the peak power periods of the two types of payloads, reduces the instantaneous power supply pressure on the satellite platform, and ensures the timestamp alignment of the imaging data of the two payloads through a unified synchronous triggering mechanism, thereby enhancing the value of multi-band infrared data collaborative application.

[0021] (3) This invention determines that after the satellite leaves the country, it stops the solidified recording step by step according to the preset shutdown sequence and cuts off the power supply to the medium- and long-wave infrared payload and the short-wave infrared payload to restore the power-off state. It calculates the total duration of the entire process from the base time point to the end of the power-off and ensures that the total duration of the entire process is strictly less than the current satellite orbit period by modifying the time interval parameter through ground annotation. This realizes zero power consumption management during non-imaging periods and automatic clearing of autonomous process execution records. At the same time, through the closed-loop constraint mechanism of the entire process duration and orbit period, it effectively prevents the timing overlap and conflict of adjacent orbit cycles due to orbital altitude attenuation, and ensures that the effective imaging time over the country is greater than the preset minimum imaging duration threshold. It has high autonomy, high reliability and long-term on-orbit adaptive capability. Attached Figure Description

[0022] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of preferred embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit the invention.

[0023] Figure 1 This is a flowchart of an on-orbit autonomous imaging control method for a satellite infrared camera according to the present invention. Detailed Implementation

[0024] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention. Obviously, the described embodiments are only some, not all, of the embodiments described in this application. All other embodiments obtained by those skilled in the art based on the embodiments in this application without creative effort are within the scope of protection of this application.

[0025] Those skilled in the art will understand that, unless otherwise stated, the singular forms “a” and “an” used herein, and “the”, may also include the plural forms. It should be further understood that the term “comprising” as used in this specification means the presence of the stated features, integers, steps, operations, elements, and / or components, but does not exclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and / or groups thereof.

[0026] First Embodiment Please see Figure 1 As shown, this embodiment provides an on-orbit autonomous imaging control method for a satellite infrared camera, including the following steps: S1: Preset the infrared camera power-off state and entry / exit criteria parameters. During the satellite's on-orbit operation, the satellite orbit position information is acquired in real time at a sampling rate of 1Hz. Kalman filtering is used to fuse GPS measured data and on-board orbit prediction data. Spatial and temporal dual confirmation is performed according to the preset entry / exit criteria. When the preset latitude and longitude boundary conditions are met and the conditions are met continuously within a set time window (4s), it is recorded as the base time point. Specifically, in this embodiment, before performing the autonomous imaging task, the infrared camera is set to the power-off state by default (i.e., all payloads are powered off), and the entry / exit criteria parameters are preset by ground data recording.

[0027] Preferably, in step S1, the entry / exit criterion parameters include preset latitude boundary value BW1, preset latitude boundary value BW2, preset first longitude boundary value DJ1 (east longitude), preset second longitude boundary value DJ2 (east longitude), and preset third longitude boundary value DJ3 (east longitude): Among them, the North latitude boundary value and the South latitude boundary value are used to define the latitude trigger lines of the ascending and descending orbit crossing criteria, respectively, and the first longitude boundary value, the second longitude boundary value and the third longitude boundary value are used to define the longitude range that is allowed to be triggered in the ascending and descending orbit criteria. All entry and exit criteria parameters can be modified in orbit via ground-based data entry to adapt to the dynamic adjustment requirements of trigger boundaries for missions at different orbital altitudes or in different border areas.

[0028] Preferably, in step S1, spatial and temporal dual confirmation is performed according to preset entry and exit criteria. When preset latitude and longitude boundary conditions are met and these conditions are met continuously within a set time window, the time point is recorded as the base time point, including: When a satellite descends (moving from north to south) and crosses a preset south latitude boundary with its longitude within a preset first longitude interval, or ascends and crosses a preset north latitude boundary with its longitude within a preset second longitude interval, and the preset time window meets the corresponding latitude and longitude conditions, it is determined to be a valid trigger and recorded as a base time point. Specifically, in this embodiment, when the satellite detects for 4 consecutive seconds that its latitude is ≤ the preset south latitude boundary value of 22°S and its longitude is between the preset first longitude interval of 75°E and 105°E, it is determined to be a valid trigger and the current time is recorded as the base time point; when the satellite ascends (moving from south to north) and detects for 4 consecutive seconds that its latitude is ≥ the preset north latitude boundary value of 42°N and its longitude is between the preset second longitude interval of 75°E and 135°E, it is also determined to be a valid trigger and recorded as a base time point; When the GPS measured data is lost or the data validity is abnormal (such as positioning error caused by interference), it automatically switches to the extrapolation mode based on the onboard orbit prediction data. At this time, the Kalman filter only performs time updates (position extrapolation based on the orbit dynamics model) and no longer performs measurement updates. Combined with the preset time window (4 seconds) confirmation mechanism, the influence of single-point noise caused by instantaneous jitter in orbit positioning or GPS loss of lock is eliminated.

[0029] The orbital position information comes from two independent data channels: measured positioning data output from the GPS receiver, and predicted data based on two-row element extrapolation by the onboard orbital prediction module. The onboard computer uses a Kalman filter to fuse the two orbital data streams. The specific operating mode is as follows: Standard fusion mode: When GPS positioning is valid (3D positioning is valid and the number of visible satellites is ≥4), time updates are performed using satellite-borne orbit prediction data as the prior estimate for the filter, and measurement updates are performed using actual GPS data as the observation value. By calculating the residual between the actual and predicted GPS values, and combining it with the preset GPS noise covariance matrix and prediction error covariance matrix, the Kalman gain is calculated to obtain the filtered posterior estimate as the current optimal orbit position. In this mode, the filter effectively suppresses GPS random noise and corrects long-term drift in orbit prediction.

[0030] Based on the high-confidence current valid location (Latitude Lat, Longitude Lon, and direction of movement marker Dir) obtained after fusion processing, the entry and exit criteria logic of dual spatial and temporal confirmation is executed: Spatial Dimension Confirmation: The current valid location is simultaneously sent to two independent geofence logic comparators; Comparator A (ascending trajectory trigger logic channel): When Dir is ascending trajectory, the absolute value of the difference between Lat and the preset North Latitude boundary BW1 is less than the preset convergence threshold, and Lon is within the closed interval [DJ1, DJ3], the trigger signal Trig_A=1 is output; Comparator B (descending trajectory trigger logic channel): When Dir is descending trajectory, the absolute value of the difference between Lat and the preset South Latitude boundary BW2 is less than the preset convergence threshold, and Lon is within the closed interval [DJ1, DJ2], the trigger signal Trig_B=1 is output.

[0031] Time-dimensional confirmation: For Trig_A or Trig_B signals, a continuous counting state machine is introduced for time window confirmation. If the trigger signal is 1 in each sampling period, the counter Confirm_Cnt increments by 1; if the trigger signal is 0, the counter is immediately forced to zero. A valid trigger is determined and the absolute time value of the current system clock is recorded as the base time point only when the count value of Confirm_Cnt reaches a preset threshold for the number of consecutive samples (in this embodiment, the sampling rate is 1Hz, and 4 consecutive counts represent 4 consecutive seconds of meeting the condition).

[0032] Since the infrared camera's startup preparation time is a fixed time before entry and shooting, and the entry time cannot be accurately determined in advance by the satellite, this embodiment uses the time when the most recent previous orbit crossed a certain latitude line as an auxiliary criterion, i.e., the aforementioned base time point recording mechanism. After the base time point is recorded, a trigger shielding flag is immediately set, and no new trigger signals will be responded to during the same transit process.

[0033] S2: Based on the base time point, power-on commands are sent in a time-sharing manner according to different preset time intervals. The startup and parameter configuration sub-processes of the mid-to-long-wave infrared payload and the short-wave infrared payload are executed in a staggered manner. After the image windowing configuration is completed, the mid-to-long-wave infrared payload and the short-wave infrared payload are controlled to enter the imaging mode synchronously and the solid-state recording function is enabled. Specifically, in this embodiment, the mid-to-long-wave and short-wave payloads adopt the time-sharing startup and fixed interval timing coordination principle. The thermal control setup time and cooling setup time of the two types of payloads are different. The staggered peak power can reduce the instantaneous power consumption of the satellite platform. Mutual interference is avoided, and the collaborative imaging is only entered after the respective states are stable.

[0034] Preferably, in step S2, based on the base time point, power-on commands are sent at different preset time intervals to stagger the execution of the start-up and parameter configuration sub-processes for the medium- and long-wave infrared loads and the short-wave infrared loads, including: At the base time point + T1 (the number of injectable counts can be modified, default 57 min) (the camera needs to be pre-activated 20 min before formal imaging to make the temperatures of each component inside the camera reach stability), send a power-on command for the mid-wave and long-wave infrared payload, making the mid-wave and long-wave infrared payload enter the low-power mode and the shutter always closed. 20 s after power-on, sequentially send a time calibration command, a temperature control target temperature command, and a thermal insulation mode command. Specifically, in this embodiment, 20 s after power-on, send a mid-wave and long-wave infrared time calibration command (command code: 2A 00 08 00 00); 2 s after time calibration, send a mid-wave and long-wave infrared temperature control target temperature command (example code: 2A 01 07 00 19, corresponding to 25 °C); 2 s after the temperature control command is sent, send a mid-wave and long-wave infrared thermal insulation mode command (command code: 10 02 02). The payload shutter is corrected twice, and the shutter closes after 40 s, entering the thermal insulation mode; At the base time point + T2 (the number of injectable counts can be modified, default 77 min), send a power-on command for the short-wave infrared payload, making the short-wave infrared payload enter the low-power mode and the shutter always closed. Specifically, in this embodiment, 20 s after power-on, send a power-on command for the short-wave infrared low-power mode power supply (command code: 03 01 05 00 00 00 01), and the payload shutter opens; then every 2 s interval, sequentially send a short-wave infrared gain setting command (default low gain, command code: 03 03 01 00 00 00 02), an integration time setting command (default 800 us, command code: 03 02 02 00 00 03 20), an internal trigger frame rate setting command (default 5 fps, command code: 03 02 03 00 00 00 32), a TEC temperature setting command (default 25 °C, command code: 03 01 05 00 00 09 c4), a TEC refrigeration function activation command (command code: 03 01 02 00 00 00 01); Where T1 and T2 are timing interval parameters modified by ground injection counts, and T1 < T2 to stagger the peak power times of the thermal control establishment and refrigeration activation of the two types of payloads.

[0035] Preferably, in step S2, after completing the image window configuration, control the mid-wave and long-wave infrared payload and the short-wave infrared payload to enter the imaging mode synchronously, including: After the short-wave infrared payload is powered on, sequentially send a power-on command for the low-power mode power supply, a gain setting command, an integration time setting command, an internal trigger frame rate setting command, a TEC temperature setting command, and a TEC refrigeration function activation command to complete the parameter configuration of the short-wave infrared payload. Specifically, in this embodiment, 1 s after the short-wave infrared payload starts up, send a mid-wave and long-wave infrared shutter correction command (command code: 2A 00 01 00 00); After the shortwave infrared payload is started, a mid-to-longwave infrared shutter correction command is sent. After correction, BAND1 to BAND4 start line commands and output line number commands are sent sequentially to achieve image windowing acquisition of the specified area and improve imaging efficiency. Specifically, in this embodiment, 10 seconds after correction, BAND1 to BAND4 start line commands are sent sequentially (command codes are 2A 01 0E 00 00, 2A 01 0F 01 18, 2A 01 10 02 BC, and 2A 01 11 03 E1, respectively). One second after BAND4 start line command is sent, output line number command (command code: 2A 01 14 00 1E) is sent to complete image windowing configuration. After the windowing configuration is completed, the mid-to-long-wave infrared (MTB) and short-wave infrared (SWI) solid-state storage recording functions are started sequentially at preset time intervals. Imaging mode commands and imaging function activation commands are sent respectively, enabling the MTB and SWI payloads to enter imaging mode synchronously and in parallel. Specifically, in this embodiment, 7 seconds after the windowing configuration is completed, the solid-state storage MTB camera data recording function is activated. 3 seconds after activation, a MTB imaging mode command (command code: 10 03 03) is sent, and the MTB payload begins recording image data. 6 seconds after entering MTB imaging mode, the solid-state storage SWI camera data recording function is activated. 3 seconds after short-wave storage activation, a short-wave infrared imaging function activation command (command code: 0301 01 00 00 00 01) is sent, and the short-wave infrared payload enters normally open shutter mode and begins imaging the Earth. Thus, the MTB and SWI payloads enter imaging mode synchronously and in parallel. During imaging, the satellite is over the national border, and the payloads maintain normal operating conditions.

[0036] S3: After determining that the satellite has left the country's airspace, stop the solidified records step by step according to the preset shutdown sequence and cut off the power supply to the medium- and long-wave infrared payloads and the short-wave infrared payloads to restore the power-off state. Calculate the total duration of the entire process from the base time point to the end of the power-off. Modify the time interval parameters through ground annotation to ensure that the total duration of the entire process is strictly less than the current satellite orbit period.

[0037] Preferably, in step S3, after determining that the satellite has left the country's airspace, the power supply to the medium- and long-wave infrared payloads and the short-wave infrared payloads is cut off in a preset shutdown sequence to restore the power-off state. First, the mid-to-long-wave infrared payload is controlled to enter the heat preservation mode, and the mid-to-long-wave infrared solid-state storage recording is stopped. Specifically, in this embodiment, 15 minutes after the short-wave infrared imaging function is turned on, a mid-to-long-wave infrared heat preservation mode command (command code: 10 02 02) is sent; 5 seconds later, the solid-state storage mid-to-long-wave infrared camera data recording is stopped. The imaging and TEC cooling functions of the shortwave infrared payload are sequentially turned off, shortwave infrared solid-state storage recording is stopped, and the power supply to the shortwave low-power mode is turned off to put it into standby mode. After a delay, the power supply to the shortwave infrared payload is cut off. Specifically, in this embodiment, 1 second after the medium- and long-wave solid-state storage stops recording, a shortwave infrared imaging function shutdown command is sent (command code: 03 01 0100 00 00 00); 2 seconds later, a shortwave infrared TEC cooling function shutdown command is sent (command code: 03 01 02 00 00 0000); 1 second later, solid-state storage shortwave infrared camera data recording is stopped; 1 second later, a shortwave infrared low-power mode power supply shutdown command is sent (command code: 03 01 05 00 00 00 00), the payload shutter closes, and it enters standby mode; 10 seconds later, a shortwave infrared payload power-down command is sent, cutting off the power supply to the shortwave infrared payload. After the short-wave infrared payload is powered off, the mid- and long-wave infrared payload is controlled to enter standby mode. After a delay, the power supply to the mid- and long-wave infrared payload is cut off, so that the infrared camera returns to the power-off state and the number of executed autonomous process instructions is cleared to zero. Specifically, in this embodiment, 21 seconds after the short-wave infrared payload is powered off, a mid- and long-wave infrared standby mode instruction (instruction code: 1001 01) is sent, and the payload shutter closes; 2 seconds later, a mid- and long-wave infrared payload power-off instruction is sent to cut off the power supply to the mid- and long-wave infrared payload.

[0038] Preferably, in step S3, the total duration of the entire process from the base time point to the end of the power outage is calculated, and the time interval parameter is modified by ground data to ensure that the total duration of the entire process is strictly less than the current satellite orbital period, including: When the satellite orbital period shortens due to orbital altitude decay, causing the original total duration of the entire process to no longer meet the constraint of being less than the current satellite orbital period, the waiting delay parameters in the T1 and T2 time interval parameters and the shutdown time sequence are compressed by ground data compression. This ensures that the single autonomous control process is completely completed before the arrival of the next orbital base time point, preventing time overlap and conflict between processes in adjacent orbital orbits. At the same time, it ensures that the effective imaging time over the national border is greater than the preset minimum imaging duration threshold (e.g., 13 minutes).

[0039] Preferably, modifying the time interval parameter by ground injection count includes: The variable parameter instructions are separated from the main autonomous control process code and stored independently in the dedicated storage space address of the satellite platform. When executing the autonomous process, variable parameter instructions are read from the dedicated storage space address in real time as needed. After the timing interval parameters and load condition parameters in the dedicated storage space address are modified by ground data, the updated parameters are automatically read and applied the next time the autonomous process is triggered, so as to adapt to the shooting quality adjustment needs caused by device degradation or target characteristic prediction errors.

[0040] Second Embodiment In this embodiment, a computer device is provided, including a memory and one or more processors. The memory stores computer code, and when the computer code is executed by one or more processors, the one or more processors cause the one or more processors to perform the steps of the on-orbit autonomous imaging control method for a satellite infrared camera in the first embodiment.

[0041] In some embodiments of this application, a computer-readable storage medium is also provided, wherein when the computer-readable instructions are executed by one or more processors, the one or more processors perform the steps of a satellite infrared camera on-orbit autonomous imaging control method as described in any one of the first embodiments.

[0042] It is understood that, for the aforementioned on-orbit autonomous imaging control method for a satellite infrared camera, if all components are implemented as software functional modules and sold or used as independent products, they can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of this invention, in essence, or the part that contributes to the prior art, or all or part of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions to cause a computer device (which may be a personal computer server or a network device, etc.) to execute all or part of the steps of the methods in the various embodiments of this invention. The aforementioned storage medium includes various media capable of storing program code, such as USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, or optical disks.

[0043] Computer-readable storage media may include data signals propagated in baseband or as part of a carrier wave, carrying readable program code. Such propagated data signals may take various forms, including but not limited to electromagnetic signals, optical signals, or any suitable combination thereof. A readable storage medium may also be any readable medium other than a readable storage medium that can transmit, propagate, or transfer a program for use by or in connection with an instruction execution system, apparatus, or device. The program code contained on the readable storage medium may be transmitted using any suitable medium, including but not limited to wireless, wired, optical fiber, RF, etc., or any suitable combination thereof.

[0044] The above description is merely a preferred embodiment of the present invention. The scope of protection of the present invention is not limited to the above embodiments. All technical solutions falling within the scope of the present invention's concept are within the scope of protection of the present invention. It should be noted that for those skilled in the art, any improvements and modifications made without departing from the principles of the present invention should also be considered within the scope of protection of the present invention.

Claims

1. A method for on-orbit autonomous imaging control of a satellite infrared camera, characterized in that, It includes the following steps: S1: Preset the power-off state of the infrared camera and the entry / exit judgment criterion parameters, obtain the satellite orbit position information in real time, use Kalman filtering to fuse the GPS measured data and the on-board orbit prediction data, and perform double confirmation in terms of space and time according to the preset entry / exit judgment criterion. When the preset latitude and longitude boundary conditions are met and the conditions are met within a continuous set time window, record it as the base time point; S2: Based on the base time point, send power-on commands at different preset time intervals in a time-sharing manner, stagger the execution of the startup and parameter configuration sub-processes of the mid-wave infrared payload and the short-wave infrared payload. After completing the image window configuration, control the mid-wave infrared payload and the short-wave infrared payload to enter the imaging mode synchronously, and enable the solid-state recording function; S3: After judging that the satellite has flown out of the national border上空, stop the solid-state recording step by step according to the preset shutdown timing sequence and cut off the power supply of the mid-wave infrared payload and the short-wave infrared payload to restore the power-off state. Calculate the total duration of the entire process from the base time point to the end of power-off, and modify the time interval parameter through ground injection to ensure that the total duration of the entire process is strictly less than the current satellite orbit period.

2. The on-orbit autonomous imaging control method for a satellite infrared camera according to claim 1, characterized in that, In step S1, performing double confirmation in terms of space and time according to the preset entry / exit judgment criterion and recording it as the base time point when the preset latitude and longitude boundary conditions are met and the conditions are met within a continuous set time window includes: When the satellite descends through the preset south latitude boundary and the longitude is within the preset first longitude interval, or ascends through the preset north latitude boundary and the longitude is within the preset second longitude interval, and the preset time window meets the corresponding latitude and longitude conditions, it is determined as an effective trigger and recorded as the base time point; When the GPS measured data is unlocked or the data validity is abnormal, automatically switch to the extrapolation mode based mainly on the on-board orbit prediction data. At this time, Kalman filtering only performs time update and no longer performs measurement update. Combining the preset time window confirmation mechanism, eliminate the influence of single-point noise caused by instantaneous jitter of orbit positioning or GPS unlocking abnormality.

3. The on-orbit autonomous imaging control method for a satellite infrared camera according to claim 1, characterized in that, In step S2, based on the base time point, sending power-on commands at different preset time intervals in a time-sharing manner and staggering the execution of the startup and parameter configuration sub-processes of the mid-wave infrared payload and the short-wave infrared payload includes: At the base time point + T1, send a power-on command for the mid-wave infrared payload to make the mid-wave infrared payload enter the low-power mode and the shutter is always closed. After power-on, send a time calibration command, a temperature control target temperature command, and a heat preservation mode command in sequence; At the base time point + T2, send a power-on command for the short-wave infrared payload to make the short-wave infrared payload enter the low-power mode and the shutter is always closed; Where T1 and T2 are the timing interval parameters modified through ground injection, and T1 < T2 to stagger the peak power times of the thermal control establishment and refrigeration start of the two types of payloads.

4. The on-orbit autonomous imaging control method for a satellite infrared camera according to claim 1, characterized in that, In step S2, after completing the image window configuration, controlling the mid-wave infrared payload and the short-wave infrared payload to enter the imaging mode synchronously includes: After the shortwave infrared payload is powered on, it sequentially sends a low-power mode power supply start command, a gain setting command, an integration time setting command, an internal trigger frame frequency setting command, a TEC temperature setting command, and a TEC cooling function start command to complete the shortwave infrared payload parameter configuration. After the shortwave infrared payload is started, a medium- and longwave infrared shutter correction command is sent. After the correction is completed, the start line command and output line number command of BAND1 to BAND4 are sent in sequence to realize the windowed acquisition of the image in the specified area. After the windowing configuration is completed, the medium- and long-wave solid-state recording and the short-wave infrared solid-state recording are started sequentially at preset time intervals, and imaging mode commands and imaging function activation commands are sent respectively, so that the medium- and long-wave infrared payload and the short-wave infrared payload enter the imaging state synchronously and in parallel.

5. The on-orbit autonomous imaging control method for a satellite infrared camera according to claim 1, characterized in that, In step S3, after determining that the satellite has left the country's airspace, the power supply to the mid- and long-wave infrared payloads and the short-wave infrared payloads is cut off in a preset shutdown sequence to restore the power-off state. First, control the mid-to-long-wave infrared load to enter the heat preservation mode and stop the mid-to-long-wave infrared solid-state recording; The imaging function and TEC cooling function of the shortwave infrared payload are turned off in sequence, the shortwave infrared solid-state recording is stopped, the power supply of the shortwave low-power mode is turned off to put it into standby mode, and the power supply of the shortwave infrared payload is cut off after a delay. After the short-wave infrared payload is powered off, the medium- and long-wave infrared payload is controlled to enter standby mode. After a delay, the power supply to the medium- and long-wave infrared payload is cut off, so that the infrared camera returns to the power-off state and the number of executed autonomous process instructions is cleared to zero.

6. The on-orbit autonomous imaging control method for a satellite infrared camera according to claim 1, characterized in that, In step S3, the total duration of the entire process from the base time point to the end of the power outage is calculated. The time interval parameter is modified by ground-based data collection to ensure that the total duration of the entire process is strictly less than the current satellite orbital period, including: When the satellite orbital period shortens due to orbital altitude decay, causing the original total duration of the entire process to no longer meet the constraint of being less than the current satellite orbital period, the waiting delay parameters in the T1 and T2 timing interval parameters and the shutdown timing are compressed by ground data injection. This ensures that the single autonomous control process is completely completed before the arrival of the next orbital base time point, preventing timing overlap and conflict between adjacent orbital cycles, while ensuring that the effective imaging time over the national border is greater than the preset minimum imaging duration threshold.

7. The on-orbit autonomous imaging control method for a satellite infrared camera according to claim 1, characterized in that, Modifying the time interval parameter by ground injection count includes: The variable parameter instructions are separated from the main autonomous control process code and stored independently in the dedicated storage space address of the satellite platform. When executing the autonomous process, the variable parameter instructions are read from the dedicated storage space address in real time as needed. When the timing interval parameters and load condition parameters in the dedicated storage space address are modified by ground data, the updated parameters are automatically read and applied the next time the autonomous process is triggered, so as to adapt to the shooting quality adjustment needs caused by device degradation or target characteristic prediction errors.

8. The on-orbit autonomous imaging control method for a satellite infrared camera according to claim 2, characterized in that, In step S1, the entry / exit criterion parameters include preset latitude boundary values, preset latitude boundary values, preset first longitude boundary values, preset second longitude boundary values, and preset third longitude boundary values: Wherein, the North latitude boundary value and the South latitude boundary value are used to define the latitude trigger lines of the ascending and descending orbit crossing criteria, respectively, and the first longitude boundary value, the second longitude boundary value and the third longitude boundary value are used to define the longitude range that is allowed to be triggered in the ascending and descending orbit criteria; All the entry and exit criteria parameters can be modified in orbit via ground-based data entry to adapt to the dynamic adjustment requirements of trigger boundary lines for missions at different orbital altitudes or in different border areas.

9. A computer-readable storage medium, characterized in that, When the computer-readable instructions are executed by one or more processors, the one or more processors perform the steps of the on-orbit autonomous imaging control method for a satellite infrared camera as described in any one of claims 1 to 8.

10. A computer device comprising a memory and one or more processors, the memory storing computer code that, when executed by the one or more processors, causes the one or more processors to perform the steps of the on-orbit autonomous imaging control method for a satellite infrared camera as described in any one of claims 1-8.

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