A fire detection device for satellites

Abstract

This invention discloses a fire detection device for satellites, belonging to the field of aerospace remote sensing technology. The method includes: a first detection device and a second detection device installed on the satellite; the first detection device is communicatively connected to the satellite's control computer, and the second detection device is communicatively connected to the satellite's data management computer; the first detection device has a first field of view and a first resolution, used to determine the location of a fire point and send the fire point location to the control computer, so that the control computer can determine a maneuvering target based on the fire point location and send the maneuvering target to the data management computer; the data management computer is used to control the working state of the second detection device based on the maneuvering target; the second detection device has a second field of view and a second resolution, used to image the fire point under the control of the data management computer; wherein, the first field of view is larger than the second field of view, and the first resolution is lower than the second resolution. This invention, through the collaborative mechanism of the first and second detection devices, enables rapid detection and precise detailed investigation of global fire points by satellites, significantly improving observation efficiency and resource utilization.

Description

Technical Field

[0001] This invention relates to the field of aerospace remote sensing technology, and in particular to a fire detection device for satellites. Background Technology

[0002] Global fire detection is a crucial technological means to safeguard Earth's ecological security, human health, and sustainable development. Currently, with the development of satellite Earth observation technology, its application in fire detection is becoming increasingly widespread. When using satellites for fire detection, on the one hand, to achieve continuous observation of large areas, the satellite's detection equipment needs a wide coverage area and a fast response speed. On the other hand, to accurately identify and analyze detected fire points, the satellite's detection equipment needs high resolution. However, an inherent contradiction exists between these two requirements, preventing existing satellites from detecting fire points quickly and accurately.

[0003] Therefore, there is an urgent need for a fire detection device for satellites to solve the above problems. Summary of the Invention

[0004] This invention provides a fire detection device for satellites, capable of quickly identifying and accurately imaging fire points. The technical solution is as follows:

[0005] On one hand, the present invention provides a fire detection device for satellites, comprising:

[0006] A first detection device and a second detection device are installed on the satellite; the first detection device is communicatively connected to the satellite's control computer, and the second detection device is communicatively connected to the satellite's data management computer.

[0007] The first detection device has a first field of view and a first resolution, used to determine the location of the fire point, and send the fire point location to the control computer, so that the control computer can determine the moving target based on the fire point location, and send the moving target to the data management computer; the data management computer is used to control the working state of the second detection device based on the moving target;

[0008] The second detection device has a second field of view and a second resolution, and is used to image the fire point under the control of the data management computer; wherein the first field of view is greater than the second field of view, and the first resolution is lower than the second resolution.

[0009] Optionally, the first detection device is a fire sensor; the fire sensor is mounted forward on the satellite platform, and the field of view of the fire sensor is perpendicular to the direction of the satellite's movement.

[0010] Optionally, the maneuvering target includes the satellite's target pose, the imaging start time of the second detection device, and the imaging end time.

[0011] Optionally, the maneuvering target is determined in the following manner:

[0012] Based on the fire point location, adjust the position and attitude of the satellite until the line of sight of the second detection device points to the fire point location, thereby obtaining the target pose of the satellite;

[0013] Based on the satellite time when the first detection device determines the fire point location and the preset satellite maneuver time threshold, the imaging start time of the second detection device is determined;

[0014] Based on the imaging start time and preset imaging duration of the second detection device, the imaging end time of the second detection device is determined.

[0015] Optionally, the imaging start time is equal to the sum of the satellite time when the first detection device determines the fire point location and the satellite maneuver time threshold.

[0016] Optionally, the second detection device is a camera.

[0017] Optionally, the satellite is equipped with a fire point autonomous detailed investigation marker;

[0018] In response to the flag being enabled, after the first detection device identifies the fire point information and sends it to the control computer, the control computer is allowed to perform attitude maneuvers on the satellite and use the second detection device to image the fire point;

[0019] In response to the flag being disabled, after the first detection device identifies fire point information and sends it to the control computer, the control computer is not allowed to perform attitude maneuvers on the satellite, and the second detection device is not operational.

[0020] Optionally, the data management computer controls the operating state of the second detection device based on the moving target, including:

[0021] When the satellite is in the target pose and the imaging start time is reached, the data management computer controls the second detection device to be powered on.

[0022] When the imaging end time is reached, the data management computer controls the second detection device to be turned off.

[0023] On the other hand, a satellite includes a fire detection device as described in any of the preceding items.

[0024] This invention provides a fire detection device for satellites. This device employs a first detection device with a large field of view, covering a wide search area and thus quickly locating the fire point. The fire point location is then sent to a control computer, which uses this information to determine the maneuvering target and directs the line of sight of a second detection device towards the fire point. Because the second detection device has high resolution, a high-resolution image of the fire point can be obtained, improving the accuracy of fire detection. Therefore, this invention can quickly determine the fire point location and accurately image it, improving detection accuracy. Attached Figure Description

[0025] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0026] Figure 1 This is a flowchart illustrating the operation of a fire detection device for satellites, as provided in an example of the present invention.

[0027] Figure 2 This is an external view of a fire sensor provided in an embodiment of the present invention;

[0028] Figure 3 This is a schematic diagram of fire point pre-installation and prediction provided by an example of the present invention;

[0029] Figure 4 This is a control and data interaction diagram between components in a fire detection device for satellites, provided by an example of the present invention. Detailed Implementation

[0030] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are some embodiments of the present invention, but not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0031] In related technologies, detection devices with large coverage areas and those with high resolution often operate independently, lacking a collaborative mechanism. When a detection device with a large coverage area detects a suspected fire point, ground station intervention is required for mission planning before instructing the high-resolution detection device to perform imaging. This results in long response times and low efficiency. Furthermore, high-resolution payloads typically need to image the entire orbit, generating a large amount of useless data and leading to low resource utilization.

[0032] Based on this, the inventive concept of this invention lies in: by employing a first detection device with a large field of view, a wider search range can be covered, thereby quickly locating the fire point. Then, after the fire point location is sent to the control computer, the control computer determines the moving target based on this, causing the line of sight of the second detection device to point towards the fire point. Because the second detection device has high resolution, a high-resolution image of the fire point can be obtained, improving the accuracy of fire point detection. Therefore, this application can quickly determine the fire point location and accurately image the fire point, improving the accuracy of detection.

[0033] The specific implementation of the above concept is described below.

[0034] Please refer to Figure 1 This invention provides a flowchart of a fire detection device for satellites, comprising:

[0035] The first detection device and the second detection device are installed on the satellite; the first detection device is connected in communication with the satellite's control computer, and the second detection device is connected in communication with the satellite's data management computer.

[0036] The first detection device has a first field of view and a first resolution, used to determine the location of the fire point and send the fire point location to the control computer, so that the control computer can determine the moving target based on the fire point location and send the moving target to the data management computer; the data management computer is used to control the working status of the second detection device based on the moving target;

[0037] The second detection device has a second field of view and a second resolution, and is used to image the fire point under the control of a digital tube computer; wherein, the first field of view is greater than the second field of view, and the first resolution is lower than the second resolution.

[0038] Specifically, the first detection device typically has a first field of view of no less than ±30° (total field of view greater than 60°) to ensure that a single image can cover an extremely wide ground strip, thereby achieving a high revisit frequency (e.g., scanning the globe 1-2 times per day). Based on experience, a sensor with a 60° field of view at a 500km orbit can achieve a swath width of approximately 500-600km. The first resolution is typically no higher than 100m-500m (e.g., 100m @ 500km). This device is primarily responsible for rapid, wide-area scanning to detect and initially locate fire points.

[0039] The second field of view of the second detection equipment is usually only 1°-5°, and the second resolution is usually required to be better than 5m (e.g., 2m @ 500km). The physical meaning is that when the satellite is running at an orbital altitude of 500 kilometers, the spatial resolution of its imaging equipment is 2 meters. This resolution can ensure that the specific shape of the fire, the location of the fire line, the burned area, and even individual burning points can be distinguished, providing accurate data for disaster assessment and rescue decision-making.

[0040] In this invention, a first detection device with a large field of view is first employed, which can cover a large search area, thereby quickly locating the fire point. Then, the fire point location is sent to a control computer, which uses this information to determine the moving target and directs the line of sight of a second detection device towards the fire point. Because the second detection device has high resolution, a high-resolution image of the fire point can be obtained, improving the accuracy of fire point detection. Therefore, this application can quickly determine the fire point location and accurately image it, improving detection accuracy.

[0041] about Figure 1 It should be noted that the system first enters the "Autonomous Fire Spot Detailed Investigation" mode. When the satellite's autonomous fire spot detailed investigation flag is enabled, the system initiates the autonomous detection process. The first detection device (such as a fire spot sensor) continuously scans the Earth, with the fire spot sensor's line of sight detecting a large area perpendicular to the satellite's direction of travel in real time. When a fire spot is detected, the fire spot sensor outputs the fire spot location information and its vector information within the sensor's field of view to the control computer.

[0042] After receiving the fire point information, the control computer performs mission planning: calculating the target satellite attitude required to precisely point the line of sight of the second detection device (such as a camera) at the fire point based on the fire point location; determining the imaging start time based on the satellite time at the time of fire point detection and a preset maneuver time threshold; and determining the imaging end time based on the imaging start time and a preset imaging duration. This planning information is encapsulated into a maneuver target parameter package and output to the data management computer.

[0043] Simultaneously, the control computer executes autonomous maneuver control, driving the satellite's attitude mechanism to adjust to the target orientation, ensuring the high-resolution camera accurately points at the ground fire point. The maneuver time threshold is determined based on the satellite's maximum maneuver angle and maneuverability, guaranteeing attitude stabilization is achieved before imaging begins.

[0044] Based on the received maneuvering target parameters, the computer controls the camera to power on when the satellite reaches the target pose and the imaging start time is reached; and controls the camera to power off when the imaging end time is reached. The entire power-on and power-off control process strictly follows the preset time window.

[0045] During camera operation, a detailed imaging task is performed to acquire image data of the fire point. After imaging is completed, the process ends, the satellite resumes Earth observation, and prepares to respond to the next fire event. The entire process, through the collaborative work of dual computers and precise timing control, achieves a fully automated and rapid response from fire point detection to detailed imaging, perfectly demonstrating the collaborative working mechanism of the first detection device (fire point sensor) and the second detection device (camera).

[0046] Before describing how the above steps are performed, the fire sensor of this embodiment of the invention will be explained.

[0047] like Figure 2 As shown, the fire sensor provided by this invention adopts a modular design and mainly includes the following five core parts:

[0048] (1) Optical components: The optical components adopt a dual-spectral design of mid-wave infrared (MWIR) and long-wave infrared (LWIR). The mid-wave infrared band (3-5μm) is mainly used for high-temperature fire detection, while the long-wave infrared band (8-12μm) is suitable for background radiation detection at room temperature. The dual-spectral design works in tandem to effectively distinguish between real fire points and false targets by comparing radiation characteristics, significantly improving the accuracy and reliability of fire point identification.

[0049] (2) The shutter calibration component uses a domestically produced electromagnetic calibration mechanism. The polarity of the electromagnetic field of the electromagnetic coil is controlled by the polarity of the input current to achieve precise opening and closing of the shutter component. This component periodically performs response consistency calibration on the infrared detector pixels to ensure the accuracy and stability of the detection data. The calibration cycle can be adjusted on-orbit via command; the default setting is one full-field calibration per track.

[0050] (3) The mechanical structure components are made of high-strength aluminum alloy material and are manufactured through precision machining and heat treatment processes. The structural design adopts a three-point support method, which fully considers the matching of thermal expansion coefficients and thermal deformation control to ensure the stability and pointing accuracy of the optical system under varying temperature conditions on the track.

[0051] (4) Circuit components, comprising four functional modules:

[0052] The SOC circuit uses a domestically produced processor to run application software and complete functions such as fire detection algorithm processing, telemetry data packaging, and system control.

[0053] The FPGA circuit implements functions such as driving timing control of dual infrared detectors, exposure parameter configuration, image acquisition and storage, image preprocessing, non-uniformity correction, shutter assembly control, and precise TEC temperature control.

[0054] The BU circuit implements bus (e.g., 1553B) communication functions and is responsible for data interaction with the satellite platform;

[0055] The PS circuit converts the primary power supply (e.g., 28V) provided by the satellite platform into the secondary power supply (e.g., 3.3V, 5V, ±12V) required by each component, and has overcurrent, overvoltage, and reverse connection protection functions.

[0056] (5) Software configuration items, including FPGA software and application software:

[0057] The FPGA software is responsible for the low-level operations of the infrared detector, such as precise timing control, shooting parameter configuration, image preprocessing, OOC correction, two-point correction, and image downlink.

[0058] The application software is based on multispectral image features and realizes functions such as intelligent algorithm processing for fire detection and cloud discrimination, telemetry data packaging, bus (such as 1553B) communication, and on-orbit maintenance.

[0059] The invention will now be described in terms of the forward-looking installation and spatial geometry of the fire sensor, as well as the information flow and control relationship of the system.

[0060] Please see Figure 3 As shown in the figure, the satellite control subsystem operates in normal Earth-orbit mode for extended periods in orbit, establishing the following spatial coordinate system: the satellite's +Z axis always points towards the Earth's center, the +X axis runs along the satellite's forward direction, and the +Y axis, +X axis, and +Z axis form a right-handed rectangular coordinate system. Within this coordinate system, the fire sensor is mounted forward-facing, with its optical axis forming a preset forward-looking angle with the +X axis (forward direction). This mounting configuration enables the fire sensor to detect fires in a large area in front of the satellite's nadir in real time, reserving a valuable time window for subsequent attitude maneuvers and detailed imaging by detecting fire targets along the flight path in advance.

[0061] Figure 4 The system's information flow and control relationships are described in detail. As shown in the figure, the system adopts a hierarchical collaborative architecture: the fire sensor sends the detected fire point location information to the control computer; the control computer calculates the satellite target attitude and imaging time window based on the fire point coordinates, generates a maneuvering target parameter packet containing the target attitude, imaging start time, and end time, and controls the satellite to perform maneuvers; after receiving these parameters, the data management computer controls the camera's on / off operation according to a precise time sequence. The entire information flow adopts a two-way confirmation mechanism, and the hardware and software states are synchronized through status registers to ensure reliable connection between each link.

[0062] This application also provides a satellite, including the fire detection device described in any of the above embodiments.

[0063] It is understood that the fire detection device in the satellite provided in this embodiment has the same function and beneficial effects as the fire detection device provided in the above embodiments, and will not be described in detail here.

[0064] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0065] Those skilled in the art will understand that all or part of the steps of the above method embodiments can be implemented by hardware related to program instructions. The aforementioned program can be stored in a computer-readable storage medium. When the program is executed, it performs the steps of the above method embodiments. The aforementioned storage medium includes various media that can store program code, such as ROM, RAM, magnetic disk, or optical disk.

[0066] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A fire detection device for satellites, characterized in that, include: The first and second detection devices installed on the satellite; The first detection device is communicatively connected to the control computer of the satellite, and the second detection device is communicatively connected to the data management computer of the satellite; The first detection device has a first field of view and a first resolution, used to determine the location of the fire point, and send the fire point location to the control computer, so that the control computer can determine the moving target based on the fire point location, and send the moving target to the data management computer; the data management computer is used to control the working state of the second detection device based on the moving target; The second detection device has a second field of view and a second resolution, and is used to image the fire point under the control of the data management computer; wherein, the first field of view is greater than the second field of view, and the first resolution is lower than the second resolution; The maneuvering target includes the satellite's target pose, the imaging start time of the second detection device, and the imaging end time; The maneuvering target was determined in the following manner: Based on the fire point location, adjust the position and attitude of the satellite until the line of sight of the second detection device points to the fire point location, thereby obtaining the target pose of the satellite; Based on the satellite time when the first detection device determines the fire point location and the preset satellite maneuver time threshold, the imaging start time of the second detection device is determined; Based on the imaging start time and preset imaging duration of the second detection device, the imaging end time of the second detection device is determined.

2. The fire detection device according to claim 1, characterized in that, The first detection device is a fire sensor; the fire sensor is mounted forward on the satellite platform, and the field of view of the fire sensor is perpendicular to the direction of the satellite's movement.

3. The fire detection device according to claim 1, characterized in that, The imaging start time is equal to the sum of the satellite time when the first detection device determines the fire point location and the satellite maneuver time threshold.

4. The fire detection device according to claim 1, characterized in that, The satellite maneuver time threshold is determined based on the maximum maneuver angle and maneuver capability of the first detection device.

5. The fire detection device according to claim 1, characterized in that, The second detection device is a camera.

6. The fire detection device according to claim 1, characterized in that, The satellite is equipped with a fire point autonomous detailed investigation marker. In response to the flag being enabled, after the first detection device identifies the fire point information and sends it to the control computer, the control computer is allowed to perform attitude maneuvers on the satellite and use the second detection device to image the fire point; In response to the flag being disabled, after the first detection device identifies fire point information and sends it to the control computer, the control computer is not allowed to perform attitude maneuvers on the satellite, and the second detection device is not operational.

7. The fire detection device according to claim 1, characterized in that, The data management computer controls the operating status of the second detection device based on the moving target, including: When the satellite is in the target pose and the imaging start time is reached, the data management computer controls the second detection device to be powered on. When the imaging end time is reached, the data management computer controls the second detection device to be turned off.

8. A satellite, characterized in that, Includes the fire detection device as described in any one of claims 1-7.

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