A static polarity verification method and system for a fire detection system

Abstract

This invention relates to the field of satellite technology, and particularly to a static polarity verification method and system for a fire detection system. The static polarity verification method for a fire detection system includes: establishing a reference mirror coordinate system based on the probe reference mirror of the fire detector; using a fire simulator to output directional thermal radiation to the center point and the four quadrants respectively, observing the vector information of the fire point in the reference mirror coordinate system to determine whether the polarity of the fire detector is correct; installing the fire detector with correct polarity on the satellite; simulating satellite operation under a satellite dynamics model, using the fire simulator to output directional thermal radiation to the center point and the four quadrants respectively, and comparing the latitude and longitude information of the fire point with the latitude and longitude information of the nadir point when the satellite is ascending and descending, respectively, to determine whether the polarity of the fire detection system is correct. This invention provides a static polarity verification method and system for a fire detection system, capable of verifying the correctness of the polarity of the fire detection system.

Description

Technical Field

[0001] This invention relates to the field of satellite technology, and in particular to a static polarity verification method and system for a fire detection system. Background Technology

[0002] Satellites equipped with fire detection systems can monitor fire information on the Earth's surface, including the coordinates of the fire points.

[0003] However, if the polarity of the fire detection system is incorrect, the coordinates in the detected fire point information will be incorrect. Therefore, it is necessary to verify the correctness of the fire detection system's polarity before launching the satellite. Currently, there is a lack of a method to verify the correctness of the fire detection system's polarity. Summary of the Invention

[0004] This invention provides a static polarity verification method and system for a fire detection system, which can verify whether the polarity of the fire detection system is correct.

[0005] In a first aspect, embodiments of the present invention provide a static polarity verification method for a fire detection system, comprising:

[0006] A reference mirror coordinate system is established based on the reference mirror of the fire detector sensor; wherein, the origin of the reference mirror coordinate system is the center point of the reference mirror, and the reference mirror coordinate system includes a first coordinate axis and a second coordinate axis that are perpendicular to each other, and the first axis and the second axis divide the reference mirror of the probe into four quadrants with equal areas;

[0007] Using a fire simulator, directional thermal radiation is output to the center point and the four quadrants respectively. The vector information of the fire point in the reference mirror coordinate system is observed to determine whether the polarity of the fire detector is correct.

[0008] Install the fire detector sensor with the correct polarity on the satellite;

[0009] The satellite's operation is simulated under a satellite dynamics model. A fire point simulator is used to output directional thermal radiation to the center point and the four quadrants respectively. When the satellite is ascending and descending, the latitude and longitude information of the fire point and the latitude and longitude information of the nadir point are compared to determine whether the polarity of the fire point detection system is correct.

[0010] In one possible design, the first and second coordinate axes divide the probe reference mirror into four quadrants of equal area, including:

[0011] The origin of the coordinate system divides the first coordinate axis and the second coordinate axis into positive and negative half axes, respectively; wherein, the value on the first coordinate axis is represented by X, and the value on the second coordinate axis is represented by Y;

[0012] The positive half-axis of the first coordinate axis, the positive half-axis of the second coordinate axis, and the edge of the probe reference mirror form the first quadrant;

[0013] The negative half-axis of the first coordinate axis, the positive half-axis of the second coordinate axis, and the edge of the probe reference mirror form the second quadrant;

[0014] The negative half-axis of the first coordinate axis, the negative half-axis of the second coordinate axis, and the edge of the probe reference mirror form the third quadrant;

[0015] The positive half-axis of the first coordinate axis, the negative half-axis of the second coordinate axis, and the edge of the probe reference mirror form the fourth quadrant;

[0016] The step of using a fire simulator to output directional thermal radiation to the center point and the four quadrants respectively, and observing the vector information of the fire point in the reference mirror coordinate system to determine whether the polarity of the fire detector is correct includes:

[0017] The center point is output with directional thermal radiation using a fire simulator to obtain vector values ​​X0 and Y0;

[0018] Using the fire simulator, directional thermal radiation is sequentially output to each point in the first quadrant to obtain multiple vector values ​​X1 and Y1.

[0019] Using the fire simulator, directional thermal radiation is sequentially output to each point in the second quadrant to obtain multiple vector values ​​X2 and Y2.

[0020] Using the fire simulator, directional thermal radiation is sequentially output to each point in the third quadrant to obtain multiple vector values ​​X3 and Y3;

[0021] Using the fire simulator, directional thermal radiation is sequentially output to each point in the fourth quadrant to obtain multiple vector values ​​X4 and Y4.

[0022] If X0 = 0, Y0 = 0, and X1 > 0, Y1 > 0, and X2 < 0, Y2 > 0, and X3 < 0, Y3 < 0, and X4 > 0, Y4 < 0, then the polarity of the fire detector is correct; otherwise, the polarity is incorrect.

[0023] In one possible design, the fire detector sensor with the correct polarity is mounted on the satellite with the following orientation:

[0024] The orientation of the probe reference mirror is consistent with the Z-axis direction during satellite operation. The direction of the first coordinate axis is opposite to the Y-axis direction during satellite operation, and the direction of the second coordinate axis is the same as the X-axis. The X-axis, Y-axis, and Z-axis are three coordinate axes in the whole satellite coordinate system. The origin of the whole satellite coordinate system is the theoretical center of the satellite-rocket separation surface. The X-axis passes through the origin, is perpendicular to the satellite-rocket separation surface, and points in the normal forward direction of satellite flight. The Z-axis passes through the origin, is located within the satellite-rocket separation surface, and points in the normal Earth-facing direction of satellite flight. The Y-axis is located within the satellite-rocket separation surface and forms a right-handed coordinate system with the X-axis and Z-axis.

[0025] In one possible design, the fire point simulator outputs directional thermal radiation to the center point and the four quadrants respectively. When the satellite is ascending and descending, the latitude and longitude information of the fire point is compared with the latitude and longitude information of the nadir point to determine whether the polarity of the fire point detection system is correct, including:

[0026] When the satellite is launched into orbit, the fire point sensor outputs directional thermal radiation to the center point. If the longitude of the fire point is equal to the longitude of the nadir point and the latitude of the fire point is equal to the latitude of the nadir point, then record P1 = 1; otherwise, record P1 = 0.

[0027] When the satellite is ascending to orbit, the fire point sensor outputs directional thermal radiation to each point in the first quadrant in sequence. If the longitude of the fire point is greater than the longitude of the nadir point and the latitude of the fire point is greater than the latitude of the nadir point, then record P2 = 1; otherwise, record P2 = 0.

[0028] When the satellite is launched into orbit, the fire point sensor outputs directional thermal radiation to each point in the second quadrant in sequence. If the longitude of the fire point is less than the longitude of the nadir point and the latitude of the fire point is greater than the latitude of the nadir point, then record P3=1; otherwise, record P3=0.

[0029] When the satellite is launched into orbit, the fire point sensor outputs directional thermal radiation to each point in the third quadrant in sequence. If the longitude of the fire point is less than the longitude of the nadir point and the latitude of the fire point is less than the latitude of the nadir point, then record P4=1; otherwise, record P4=0.

[0030] When the satellite is launched into orbit, the fire point sensor outputs directional thermal radiation to each point in the fourth quadrant in sequence. If the longitude of the fire point is greater than the longitude of the nadir point and the latitude of the fire point is less than the latitude of the nadir point, then record P5=1; otherwise, record P5=0.

[0031] When the satellite descends to its orbit, the fire point sensor outputs directional thermal radiation to the center point. If the longitude of the fire point is equal to the longitude of the nadir point and the latitude of the fire point is equal to the latitude of the nadir point, then record P6 = 1; otherwise, record P6 = 0.

[0032] When the satellite is lowering its orbit, the fire point sensor outputs directional thermal radiation to each point in the first quadrant in sequence. If the longitude of the fire point is less than the longitude of the nadir point and the latitude of the fire point is less than the latitude of the nadir point, then record P7=1; otherwise, record P7=0.

[0033] When the satellite is lowering its orbit, the fire point sensor outputs directional thermal radiation to each point in the second quadrant in sequence. If the longitude of the fire point is greater than the longitude of the nadir point and the latitude of the fire point is less than the latitude of the nadir point, then record P8 = 1; otherwise, record P8 = 0.

[0034] When the satellite is lowering its orbit, the fire point sensor outputs directional thermal radiation to each point in the third quadrant in sequence. If the longitude of the fire point is greater than the longitude of the nadir point and the latitude of the fire point is greater than the latitude of the nadir point, then record P9 = 1; otherwise, record P9 = 0.

[0035] When the satellite is lowering its orbit, the fire point sensor outputs directional thermal radiation to each point in the fourth quadrant in sequence. If the longitude of the fire point is greater than the longitude of the nadir point and the latitude of the fire point is greater than the latitude of the nadir point, then record P10 = 1; otherwise, record P10 = 0.

[0036] If the values ​​of P1, P2, P3, P4, P5, P6, P7, P8, P9, and P10 are all 1, then the polarity of the fire detection system is correct; otherwise, the polarity is incorrect.

[0037] Secondly, embodiments of the present invention provide a system for verifying the static polarity of a fire detection system, comprising:

[0038] A control computer is used to establish a reference mirror coordinate system based on the probe reference mirror of the fire detector, to determine whether the polarity of the fire detector is correct based on the vector information of the fire point, and to determine whether the polarity of the fire point detection system is correct based on the latitude and longitude information of the fire point and the latitude and longitude information of the sub-satellite point; wherein, the origin of the reference mirror coordinate system is the center point of the probe reference mirror, and the reference mirror coordinate system includes a first coordinate axis and a second coordinate axis that are perpendicular to each other, and the first axis and the second axis divide the probe reference mirror into four quadrants of equal area;

[0039] A fire simulator is used to output directional thermal radiation to the center point and the four quadrants respectively;

[0040] Fire detector sensors are used to output vector and latitude / longitude information of the fire location;

[0041] The satellite is used to install the fire detector sensor and output the latitude and longitude information of the sub-satellite point;

[0042] A satellite dynamics model device is used to simulate the operation of the satellite.

[0043] In one possible design, the orientation of the probe reference mirror is consistent with the Z-axis direction during satellite operation, the direction of the first coordinate axis is opposite to the Y-axis direction during satellite operation, and the direction of the second coordinate axis is the same as the X-axis. The X-axis, Y-axis, and Z-axis are three coordinate axes in a global coordinate system. The origin of the global coordinate system is the theoretical center of the satellite-launch separation surface. The X-axis passes through the origin, is perpendicular to the satellite-launch separation surface, and points in the normal forward direction of satellite flight. The Z-axis passes through the origin, is located within the satellite-launch separation surface, and points in the normal Earth-facing direction of satellite flight. The Y-axis is located within the satellite-launch separation surface and forms a right-handed coordinate system with the X-axis and Z-axis.

[0044] In one possible design, the satellite orbital parameters simulated by the satellite dynamics model device include:

[0045] The semi-major axis of the track is 6800 km;

[0046] The orbital altitude is 500km;

[0047] The tilt angle is 97°;

[0048] The eccentricity is 0;

[0049] The local time at the descending node is 10:30 am.

[0050] In one possible design, the fire simulator includes a surface blackbody, which is coupled with a collimator and a variable aperture to simulate infrared radiation characteristics of 50–500°C.

[0051] Before launching a satellite carrying a fire detection system, the polarity of the system needs to be verified. First, a reference mirror coordinate system is established based on the probe reference mirror of the fire detector. The origin of this coordinate system is the center point of the probe reference mirror, and the coordinate system includes a first and a second coordinate axis that are perpendicular to each other, dividing the probe reference mirror into four quadrants of equal area. Then, the individual polarity of the fire detector is verified using this coordinate system. Specifically, the vector information of the fire point captured by the probe reference mirror is observed using a fire simulator simulating the radiation center point of a high-temperature source and the four quadrants. The individual polarity of the fire detector is verified by comparing the actual illumination position of the fire point with the position represented by the vector information. The fire detector with the correct polarity is then installed on the satellite, and the satellite's operational data is simulated on the ground using a satellite dynamics model. During the satellite's ascent and descent, the probe reference mirror is illuminated using a fire simulator, and the polarity of the fire detection system is verified by comparing the satellite's ground-based latitude and longitude with the latitude and longitude of the fire point. Attached Figure Description

[0052] 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.

[0053] Figure 1 This is a flowchart of a static polarity verification method for a fire detection system provided in an embodiment of the present invention;

[0054] Figure 2 This is a schematic diagram of a quadrant distribution provided by the present invention;

[0055] Figure 3 This is a schematic diagram of a fire detection system provided by the present invention. Detailed Implementation

[0056] 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.

[0057] Please refer to Figure 1 This invention provides a static polarity verification method for a fire detection system, comprising:

[0058] A reference mirror coordinate system is established based on the reference mirror of the fire detector sensor. The origin of the reference mirror coordinate system is the center point of the reference mirror. The reference mirror coordinate system includes a first coordinate axis and a second coordinate axis that are perpendicular to each other. The first and second coordinate axes divide the reference mirror into four quadrants with equal areas.

[0059] Using a fire simulator, directional thermal radiation is output to the center point and the four quadrants respectively. The vector information of the fire point in the reference mirror coordinate system is observed to determine whether the polarity of the fire detector is correct.

[0060] Install the fire detector sensor with the correct polarity on the satellite;

[0061] The satellite's operation was simulated using a satellite dynamics model. A fire point simulator was used to output directional thermal radiation to the center point and the four quadrants. When the satellite was ascending and descending, the latitude and longitude information of the fire point and the latitude and longitude information of the nadir point were compared to determine whether the polarity of the fire point detection system was correct.

[0062] Before launching a satellite carrying a fire detection system, the polarity of the system needs to be verified. First, a reference mirror coordinate system is established based on the probe reference mirror of the fire detector. The origin of this coordinate system is the center point of the probe reference mirror, and the coordinate system includes a first and a second coordinate axis that are perpendicular to each other, dividing the probe reference mirror into four quadrants of equal area. Then, the individual polarity of the fire detector is verified using this coordinate system. Specifically, using a fire simulator to simulate the radiation center point of a high-temperature source and the four quadrants, the vector information of the fire point captured by the probe reference mirror is observed. The individual polarity of the fire detector is verified by comparing the actual illumination position of the fire point with the position represented by the vector information. The fire detector with the correct polarity is then installed on the satellite, and the satellite's operational data is simulated on the ground using a satellite dynamics model. During both the satellite's ascent and descent, the probe reference mirror is illuminated using a fire simulator, and the polarity of the fire detection system is verified by comparing the satellite's ground-based latitude and longitude with the latitude and longitude of the fire point.

[0063] In some embodiments of the present invention, please refer to Figure 2 The first coordinate axis Xa and the second coordinate axis Ya divide the probe reference mirror into four quadrants of equal area, including:

[0064] The origin of the coordinate system divides the first and second coordinate axes into positive and negative semi-axes, respectively; the values ​​on the first coordinate axis are represented by X, and the values ​​on the second coordinate axis are represented by Y.

[0065] The positive half-axis of the first coordinate axis, the positive half-axis of the second coordinate axis, and the edge of the probe reference mirror form the first quadrant;

[0066] The negative half-axis of the first coordinate axis, the positive half-axis of the second coordinate axis, and the edge of the probe reference mirror form the second quadrant;

[0067] The negative half-axis of the first coordinate axis, the negative half-axis of the second coordinate axis, and the edge of the probe reference mirror form the third quadrant;

[0068] The positive half-axis of the first coordinate axis, the negative half-axis of the second coordinate axis, and the edge of the probe reference mirror form the fourth quadrant;

[0069] Using a fire simulator, directional thermal radiation is output to the center point and the four quadrants respectively. The vector information of the fire point in the reference mirror coordinate system is observed to determine whether the polarity of the fire detector is correct, including:

[0070] Using a fire simulator, directional thermal radiation is output to the center point to obtain vector values ​​X0 and Y0;

[0071] Using a fire simulator, directional thermal radiation is output to each point in the first quadrant in sequence to obtain multiple vector values ​​X1 and Y1.

[0072] Using a fire simulator, directional thermal radiation is output to each point in the second quadrant in sequence to obtain multiple vector values ​​X2 and Y2.

[0073] Using a fire simulator, directional thermal radiation is output to each point in the third quadrant in sequence to obtain multiple vector values ​​X3 and Y3.

[0074] Using a fire simulator, directional thermal radiation is output to each point in the fourth quadrant in sequence to obtain multiple vector values ​​X4 and Y4.

[0075] If X0 = 0, Y0 = 0, and X1 > 0, Y1 > 0, and X2 < 0, Y2 > 0, and X3 < 0, Y3 < 0, and X4 > 0, Y4 < 0, then the polarity of the fire detector is correct; otherwise, the polarity is incorrect.

[0076] In summary, the polarity of the irradiation position and the output fire vector, as shown in Table 1, is correct.

[0077] Table 1

[0078] Location Fire vector X Fire point vector Y center point X＝0 Y＝0 First Quadrant X>0 Y>0 Second Quadrant X<0 Y>0 Third Quadrant X<0 Y<0 Fourth Quadrant X>0 Y<0

[0079] In this embodiment, before using the fire simulator to output radiation, the fire sensor probe and the fire simulator need to be fixed on the adjustable bracket, with the probe +Za axis (i.e., the direction of the probe optical axis) pointing towards the direction of the fire simulator; then power on the fire system and the fire simulator, and adjust the position of the bracket so that the high-temperature target hole of the fire simulator is aligned with the center point and four quadrants of the fire sensor probe.

[0080] In some embodiments of the present invention, please refer to Table 2, the fire detector sensor with the correct polarity is installed on the satellite with the following orientation:

[0081] The probe reference mirror is oriented Za in the same direction as the Z-axis during satellite operation. The direction of the first coordinate axis is opposite to the direction of the Y-axis during satellite operation, and the direction of the second coordinate axis is the same as the X-axis. Among them, the X-axis, Y-axis and Z-axis are three coordinate axes in the whole satellite coordinate system. The origin of the whole satellite coordinate system is the theoretical center of the satellite-rocket separation surface. The X-axis passes through the origin, is perpendicular to the satellite-rocket separation surface, and points in the normal forward direction of satellite flight. The Z-axis passes through the origin, is located in the satellite-rocket separation surface, and points in the normal direction of satellite flight towards the Earth. The Y-axis is located in the satellite-rocket separation surface and forms a right-handed system with the X-axis and Z-axis.

[0082] Table 2

[0083] Angle (°) Whole star + X-axis Full star + Y-axis Full star + Z-axis Sensor + Xa axis 90 180 90 Sensor + Ya-axis 0 90 90 Sensor + Za axis 90 90 0

[0084] Of course, fire detection systems can also be installed on satellites in other locations and orientations, and the corresponding system polarity verification standards will be adjusted accordingly. The verification standards for the installation method provided in this embodiment are the simplest and easiest to understand.

[0085] The verification method for the above installation location and orientation is as follows:

[0086] Using a fire simulator, directional thermal radiation is output for the center point and the four quadrants. The latitude and longitude information of the fire point is compared with that of the nadir point during satellite ascent and descent to determine the correctness of the fire detection system's polarity. This includes:

[0087] When the satellite is ascending to orbit, the fire point sensor outputs directional thermal radiation to the center point. If the longitude of the fire point is equal to the longitude of the nadir point and the latitude of the fire point is equal to the latitude of the nadir point, then record P1=1; otherwise, record P1=0.

[0088] When the satellite is ascending to orbit, the fire point sensor outputs directional thermal radiation to each point in the first quadrant in sequence. If the longitude of the fire point is greater than the longitude of the nadir point and the latitude of the fire point is greater than the latitude of the nadir point, then record P2=1; otherwise, record P2=0.

[0089] When the satellite is ascending to orbit, the fire point sensor outputs directional thermal radiation to each point in the second quadrant in sequence. If the longitude of the fire point is less than the longitude of the nadir point and the latitude of the fire point is greater than the latitude of the nadir point, then record P3=1; otherwise, record P3=0.

[0090] When the satellite is ascending to orbit, the fire point sensor outputs directional thermal radiation to each point in the third quadrant in sequence. If the longitude of the fire point is less than the longitude of the nadir point and the latitude of the fire point is less than the latitude of the nadir point, then record P4=1; otherwise, record P4=0.

[0091] When the satellite is ascending to orbit, the fire point sensor outputs directional thermal radiation to each point in the fourth quadrant in sequence. If the longitude of the fire point is greater than the longitude of the nadir point and the latitude of the fire point is less than the latitude of the nadir point, then record P5=1; otherwise, record P5=0.

[0092] When the satellite descends to its orbit, the fire point sensor outputs directional thermal radiation to the center point. If the longitude of the fire point is equal to the longitude of the nadir point and the latitude of the fire point is equal to the latitude of the nadir point, then record P6=1; otherwise, record P6=0.

[0093] When the satellite is lowering its orbit, the fire point sensor outputs directional thermal radiation to each point in the first quadrant in sequence. If the longitude of the fire point is less than the longitude of the nadir point and the latitude of the fire point is less than the latitude of the nadir point, then record P7=1; otherwise, record P7=0.

[0094] When the satellite is lowering its orbit, the fire point sensor outputs directional thermal radiation to each point in the second quadrant in sequence. If the longitude of the fire point is greater than the longitude of the nadir point and the latitude of the fire point is less than the latitude of the nadir point, then record P8=1; otherwise, record P8=0.

[0095] When the satellite is lowering its orbit, the fire point sensor outputs directional thermal radiation to each point in the third quadrant in sequence. If the longitude of the fire point is greater than the longitude of the nadir point and the latitude of the fire point is greater than the latitude of the nadir point, then record P9=1; otherwise, record P9=0.

[0096] When the satellite is lowering its orbit, the fire point sensor outputs directional thermal radiation to each point in the fourth quadrant in sequence. If the longitude of the fire point is greater than the longitude of the nadir point and the latitude of the fire point is greater than the latitude of the nadir point, then record P10 = 1; otherwise, record P10 = 0.

[0097] If the values ​​of P1, P2, P3, P4, P5, P6, P7, P8, P9, and P10 are all 1, then the polarity of the fire detection system is correct; otherwise, the polarity is incorrect.

[0098] The correct polarity criteria for the fire detection system are shown in Table 3:

[0099] Table 3

[0100]

[0101] Among them, L h The longitude of the fire point, δ h The latitude of the fire point.

[0102] like Figure 3 As shown, this embodiment of the invention provides a system for verifying the static polarity of a fire detection system, comprising:

[0103] The control computer is used to establish a reference mirror coordinate system based on the probe reference mirror of the fire detector, to determine whether the polarity of the fire detector is correct based on the vector information of the fire point, and to determine whether the polarity of the fire point detection system is correct based on the latitude and longitude information of the fire point and the latitude and longitude information of the sub-satellite point. The origin of the reference mirror coordinate system is the center point of the probe reference mirror, and the reference mirror coordinate system includes a first coordinate axis and a second coordinate axis that are perpendicular to each other. The first axis and the second axis divide the probe reference mirror into four quadrants with equal areas.

[0104] Fire simulator, used to output directional thermal radiation at the center point and in the four quadrants respectively;

[0105] Fire detector sensors are used to output vector and latitude / longitude information of the fire location;

[0106] The satellite is used to install fire detectors and output the latitude and longitude information of the nadir point.

[0107] Satellite dynamics model device, used to simulate satellite operation.

[0108] In some embodiments of the present invention, the orientation of the probe reference mirror is consistent with the Z-axis direction during satellite operation, the direction of the first coordinate axis is opposite to the Y-axis direction during satellite operation, and the direction of the second coordinate axis is the same as the X-axis; wherein, the X-axis, Y-axis and Z-axis are three coordinate axes in the whole satellite coordinate system, the origin of the whole satellite coordinate system is the theoretical center of the satellite-rocket separation surface, the X-axis passes through the coordinate origin, is perpendicular to the satellite-rocket separation surface, and points to the forward direction of normal satellite flight, the Z-axis passes through the coordinate origin, is located in the satellite-rocket separation surface, and points to the direction of normal satellite flight towards the Earth, and the Y-axis is located in the satellite-rocket separation surface, forming a right-handed system with the X-axis and Z-axis.

[0109] In some embodiments of the present invention, the satellite orbital parameters simulated by the satellite dynamics model device include:

[0110] The semi-major axis of the track is 6800 km;

[0111] The orbital altitude is 500km;

[0112] The tilt angle is 97°;

[0113] The eccentricity is 0;

[0114] The local time at the descending node is 10:30 am.

[0115] In some embodiments of the present invention, the fire simulator includes a surface blackbody, which, together with a collimator and a variable aperture, simulates the infrared radiation characteristics of 50–500°C.

[0116] In this embodiment, a fire simulator is used for ground polarity verification. The simulator employs a high-temperature surface source blackbody, capable of simulating the infrared radiation characteristics of objects ranging from +50°C to +500°C. Combined with a collimator and different apertures (variable apertures), it can simulate the infrared radiation characteristics of high-temperature targets. The simulator is powered directly by a 220V AC power supply, and the temperature is set using the temperature controller located in the lower right corner of the panel. A diagram of the simulator's appearance is attached. Figure 3 As shown, the circular hole is the target hole for high temperature.

[0117] 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.

[0118] 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.

[0119] 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 method of static polarity verification for a fire point detection system, the method comprising: include: A reference mirror coordinate system is established based on the reference mirror of the fire detector sensor; wherein, the origin of the reference mirror coordinate system is the center point of the reference mirror, and the reference mirror coordinate system includes a first coordinate axis and a second coordinate axis that are perpendicular to each other, and the first axis and the second axis divide the reference mirror of the probe into four quadrants with equal areas; Using a fire simulator, directional thermal radiation is output to the center point and the four quadrants respectively. The vector information of the fire point in the reference mirror coordinate system is observed to determine whether the polarity of the fire detector is correct. Install the fire detector sensor with the correct polarity on the satellite; The satellite's operation is simulated under a satellite dynamics model. A fire point simulator is used to output directional thermal radiation to the center point and the four quadrants respectively. When the satellite is ascending and descending, the latitude and longitude information of the fire point and the latitude and longitude information of the nadir point are compared to determine whether the polarity of the fire point detection system is correct.

2. The method of claim 1, wherein, The first and second coordinate axes divide the probe reference mirror into four quadrants of equal area, including: The origin of the coordinate system divides the first coordinate axis and the second coordinate axis into positive and negative half axes, respectively; wherein, the value on the first coordinate axis is represented by X, and the value on the second coordinate axis is represented by Y; The positive half-axis of the first coordinate axis, the positive half-axis of the second coordinate axis, and the edge of the probe reference mirror form the first quadrant; The negative half-axis of the first coordinate axis, the positive half-axis of the second coordinate axis, and the edge of the probe reference mirror form the second quadrant; The negative half-axis of the first coordinate axis, the negative half-axis of the second coordinate axis, and the edge of the probe reference mirror form the third quadrant; The positive half-axis of the first coordinate axis, the negative half-axis of the second coordinate axis, and the edge of the probe reference mirror form the fourth quadrant; The step of using a fire simulator to output directional thermal radiation to the center point and the four quadrants respectively, and observing the vector information of the fire point in the reference mirror coordinate system to determine whether the polarity of the fire detector is correct includes: The center point is output with directional thermal radiation using a fire simulator to obtain vector values ​​X0 and Y0; Using the fire simulator, directional thermal radiation is sequentially output to each point in the first quadrant to obtain multiple vector values ​​X1 and Y1. Using the fire simulator, directional thermal radiation is sequentially output to each point in the second quadrant to obtain multiple vector values ​​X2 and Y2. Using the fire simulator, directional thermal radiation is sequentially output to each point in the third quadrant to obtain multiple vector values ​​X3 and Y3; Using the fire simulator, directional thermal radiation is sequentially output to each point in the fourth quadrant to obtain multiple vector values ​​X4 and Y4. If X0=0, Y0=0, and X1>0, Y1>0, and X2<0, Y2>0, and X3<0, Y3<0, and X4>0, Y4<0, then the polarity of the fire detector is correct; otherwise, the polarity is incorrect.

3. The method according to claim 2, characterized in that, The fire detector sensor with the correct polarity is mounted on the satellite with the following orientation: The orientation of the probe reference mirror is consistent with the Z-axis direction during satellite operation. The direction of the first coordinate axis is opposite to the Y-axis direction during satellite operation, and the direction of the second coordinate axis is the same as the X-axis. The X-axis, Y-axis, and Z-axis are three coordinate axes in the whole satellite coordinate system. The origin of the whole satellite coordinate system is the theoretical center of the satellite-rocket separation surface. The X-axis passes through the origin, is perpendicular to the satellite-rocket separation surface, and points in the normal forward direction of satellite flight. The Z-axis passes through the origin, is located within the satellite-rocket separation surface, and points in the normal Earth-facing direction of satellite flight. The Y-axis is located within the satellite-rocket separation surface and forms a right-handed coordinate system with the X-axis and Z-axis.

4. The method according to claim 3, characterized in that, The method of using a fire simulator to output directional thermal radiation to the center point and the four quadrants, and comparing the latitude and longitude information of the fire point with that of the nadir point when the satellite is ascending and descending, respectively, to determine whether the polarity of the fire detection system is correct, includes: When the satellite is launched into orbit, the fire detector is used to output directional thermal radiation to the center point. If the longitude of the fire point is equal to the longitude of the nadir point and the latitude of the fire point is equal to the latitude of the nadir point, then P1=1 is recorded; otherwise, P1=0 is recorded. When the satellite is launched into orbit, the fire detector is used to output directional thermal radiation to each point in the first quadrant in sequence. If the longitude of the fire point is greater than the longitude of the nadir point and the latitude of the fire point is greater than the latitude of the nadir point, then P2=1 is recorded; otherwise, P2=0 is recorded. When the satellite is launched into orbit, the fire detector will output directional thermal radiation to each point in the second quadrant in sequence. If the longitude of the fire point is less than the longitude of the nadir point and the latitude of the fire point is greater than the latitude of the nadir point, then record P3=1; otherwise, record P3=0. When the satellite is launched into orbit, the fire detector will output directional thermal radiation to each point in the third quadrant in sequence. If the longitude of the fire point is less than the longitude of the nadir point and the latitude of the fire point is less than the latitude of the nadir point, then record P4=1; otherwise, record P4=0. When the satellite is launched into orbit, the fire detector will output directional thermal radiation to each point in the fourth quadrant in sequence. If the longitude of the fire point is greater than the longitude of the nadir point and the latitude of the fire point is less than the latitude of the nadir point, then record P5=1; otherwise, record P5=0. When the satellite descends to its orbit, the fire detector is used to output directional thermal radiation to the center point. If the longitude of the fire point is equal to the longitude of the nadir point and the latitude of the fire point is equal to the latitude of the nadir point, then record P6=1; otherwise, record P6=0. When the satellite is lowering its orbit, the fire detector will output directional thermal radiation to each point in the first quadrant in sequence. If the longitude of the fire point is less than the longitude of the nadir point and the latitude of the fire point is less than the latitude of the nadir point, then record P7=1; otherwise, record P7=0. When the satellite is lowering its orbit, the fire detector will output directional thermal radiation to each point in the second quadrant in sequence. If the longitude of the fire point is greater than the longitude of the nadir point and the latitude of the fire point is less than the latitude of the nadir point, then record P8=1; otherwise, record P8=0. When the satellite descends to its orbit, the fire detector is used to output directional thermal radiation to each point in the third quadrant in sequence. If the longitude of the fire point is greater than the longitude of the nadir point and the latitude of the fire point is greater than the latitude of the nadir point, then record P9=1; otherwise, record P9=0. When the satellite is lowering its orbit, the fire detector will output directional thermal radiation to each point in the fourth quadrant in sequence. If the longitude of the fire point is greater than the longitude of the nadir point and the latitude of the fire point is greater than the latitude of the nadir point, then record P10=1; otherwise, record P10=0. If the values ​​of P1, P2, P3, P4, P5, P6, P7, P8, P9, and P10 are all 1, then the polarity of the fire detection system is correct; otherwise, the polarity is incorrect.

5. A system for verifying the static polarity of a fire detection system, characterized in that, include: A control computer is used to establish a reference mirror coordinate system based on the probe reference mirror of the fire detector, to determine whether the polarity of the fire detector is correct based on the vector information of the fire point, and to determine whether the polarity of the fire point detection system is correct based on the latitude and longitude information of the fire point and the latitude and longitude information of the sub-satellite point; wherein, the origin of the reference mirror coordinate system is the center point of the probe reference mirror, and the reference mirror coordinate system includes a first coordinate axis and a second coordinate axis that are perpendicular to each other, and the first axis and the second axis divide the probe reference mirror into four quadrants of equal area; A fire simulator is used to output directional thermal radiation to the center point and the four quadrants respectively; Fire detector sensors are used to output vector and latitude / longitude information of the fire location; The satellite is used to install the fire detector sensor and output the latitude and longitude information of the sub-satellite point; A satellite dynamics model device is used to simulate the operation of the satellite.

6. The system according to claim 5, characterized in that, The orientation of the probe reference mirror is consistent with the Z-axis direction during satellite operation. The direction of the first coordinate axis is opposite to the Y-axis direction during satellite operation, and the direction of the second coordinate axis is the same as the X-axis. The X-axis, Y-axis, and Z-axis are three coordinate axes in the whole satellite coordinate system. The origin of the whole satellite coordinate system is the theoretical center of the satellite-rocket separation surface. The X-axis passes through the origin, is perpendicular to the satellite-rocket separation surface, and points in the normal forward direction of satellite flight. The Z-axis passes through the origin, is located within the satellite-rocket separation surface, and points in the normal Earth-facing direction of satellite flight. The Y-axis is located within the satellite-rocket separation surface and forms a right-handed coordinate system with the X-axis and Z-axis.

7. The system according to claim 6, characterized in that, The satellite orbital parameters simulated by the satellite dynamics model device include: The semi-major axis of the track is 6800 km; The orbital altitude is 500km; The tilt angle is 97°; The eccentricity is 0; The local time at the descending node is 10:30 am.

8. The system according to claim 7, characterized in that, The fire simulator includes a surface blackbody, which, in conjunction with a collimator and a variable aperture, simulates infrared radiation characteristics from 50 to 500°C.

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