Collaborative guidance method and system based on satellite on-orbit performance evaluation

Abstract

The invention provides a collaborative guidance method and system based on satellite on-orbit performance evaluation, and the method comprises the steps: S1, collecting the original data of a satellite, and obtaining the feature information of an observation region; s2, evaluating the observation performance of the alternative target satellites on the observation area to obtain an observation performance report; and S3, based on the observation performance report, transmitting the guide information to the target satellite meeting the observation performance requirement according to the requirement. According to the method, the observation tasks in the constellation can be planned, richer observation area feature information can be obtained, other satellites are guided to execute the observation tasks according to needs, waste of observation resources is effectively avoided, and the overall use efficiency of the constellation is improved.

Description

Technical Field

[0001] The present invention belongs to the technical field of satellite information processing. Specifically, it relates to a collaborative guidance method and system based on satellite on-orbit performance evaluation. More specifically, it is a collaborative guidance method based on satellite on-orbit performance evaluation. Background Art

[0002] With the increasing demand for data transmission, a global wave of building large-scale constellations represented by Starlink, Telesat, LeoSat, etc. is currently underway. The large-scale constellations form a backbone network through inter-satellite links such as lasers and microwaves, and can perform routing and network management without relying on ground gateways, achieving the service goal of global continuous communication. In addition, optical and microwave means have become the main ways of earth remote sensing observation.

[0003] Optical remote sensing satellites use images in spectral bands such as visible light or infrared to observe and identify surface scenes and objects. Microwave remote sensing satellites use microwaves that can penetrate clouds and surface vegetation to obtain and sense information underground.

[0004] Therefore, based on an observation layer composed of multiple remote sensing satellites such as visible light, infrared, microwave imaging, and microwave observation, and comprehensively using various remote sensing means for collaborative observation has gradually become one of the important means of future remote sensing observation.

[0005] Patent document CN118054838A discloses a heuristic-based low-earth orbit satellite constellation mission planning method and simulation system. The scheme adopted by the heuristic model-based low-earth orbit internet satellite constellation mission planning method is to obtain the mission planning requirements of the gateway station, read the ephemeris data of the internet constellation, establish a satellite overpass information matrix, plan the feeder plan matrix between the gateway station and the constellation according to the mission requirements and constraints, and integrate it into a complete time period plan slice matrix. This method can achieve efficient continuous feeder service of the internet constellation to the ground, but it does not belong to the same application scenario as constellation collaborative guidance, and it cannot avoid the waste situation of single-satellite observation losing the target or multi-satellite observation resource redundancy.

[0006] Patent document CN117764134A discloses a deep learning point target denoising method for remote sensing mission planning. This scheme calculates the mission imaging side-sway angle by orbit recursion for each satellite, determines the imaging time window, obtains the training data set, trains the point task denoising neural network to obtain the trained point task denoising neural network, but it does not belong to the same application scenario as constellation collaborative guidance, and it cannot avoid the waste situation of single-satellite observation losing the target or multi-satellite observation resource redundancy.

[0007] Patent document CN116208236B discloses a method for mission planning of a SAR satellite constellation. This solution coordinates the observation target requirements of single users and multi-users, conducts multi-satellite mission allocation, SAR payload parameter calculation, single-satellite mission planning, mission scheduling and conflict resolution, and finally executes the mission. However, it does not belong to the same application scenario as the method of collaborative guidance on-demand after on-board processing, and it is impossible to avoid the situation of losing the target in single-satellite observation or wasting redundant multi-satellite observation resources.

[0008] Patent document CN118264310A discloses a method, device and electronic equipment for mission planning of a low-earth orbit satellite Internet of Things constellation. This solution determines the conflict arcs by obtaining all visible arcs between the ground station and the satellite, and gives constraint conditions and objective functions for mission planning. It does not belong to the same application scenario as the constellation collaborative guidance method, and it is impossible to avoid the situation of losing the target in single-satellite observation or wasting redundant multi-satellite observation resources.

[0009] Patent document CN117068393A discloses a method for constellation collaborative mission planning based on hybrid expert experience replay. This solution establishes a mission planning model and a Markov decision model, designs a deep mission planning algorithm based on hybrid expert experience replay, and conducts mission planning implementation. It does not perform on-board processing on the observation area in the planning process, which is inconsistent with the constellation collaborative guidance method, and it is impossible to avoid the situation of losing the target in single-satellite observation or wasting redundant multi-satellite observation resources.

[0010] Patent document CN117217483A discloses a method for mission planning of a giant remote sensing constellation. This solution obtains the importance scores of each to-be-imaged task through an examination mechanism, determines the letter of intent based on the selection willingness scores of different satellite imaging time windows, and performs task matching according to the sorted to-be-imaged tasks and the letter of intent to generate a general mission planning scheme. It does not belong to the same application scenario as the constellation collaborative guidance method, and it is impossible to avoid the situation of losing the target in single-satellite observation or wasting redundant multi-satellite observation resources.

[0011] Patent document CN119363216A discloses a method and system for evaluating the coverage of a target area by a low-earth orbit communication constellation, including: S1. Dividing the target area of the low-earth orbit communication constellation into quadrilateral grids based on longitude and latitude lines; S2. Calculating the single-satellite coverage time series of a single point target considering the earth's curvature; S3. Statistically calculating the coverage time of the constellation for the target area by statistically calculating the coverage time of a single satellite for the target; S4. Comprehensively evaluating the coverage performance of the communication constellation for the target area through coverage indicators. This method does not belong to the same application scenario as the constellation collaborative guidance method, and it is impossible to avoid the situation of losing the target in single-satellite observation or wasting redundant multi-satellite observation resources.

[0012] In summary, the current collaborative guidance planning method for a constellation generates collaborative guidance planning information by comprehensively considering constraints such as the payload characteristics, inter-satellite links, and observation fields of view of each remote sensing satellite in the constellation, and transmits the guidance information to the corresponding remote sensing satellites to perform remote sensing observation tasks. However, for complex ground object scenes with a large number of observation areas, the current collaborative guidance planning method does not consider the on-orbit performance of the observation satellites. Mechanical execution of the collaborative guidance planning task may result in the situation of a single satellite losing the target during observation or redundant waste of multi-satellite observation resources, and the overall utilization efficiency of the constellation cannot be fully exerted. This problem urgently needs to be solved. Summary of the Invention

[0013] Aiming at the defects in the prior art, the purpose of the present invention is to provide a collaborative guidance method and system based on satellite on-orbit performance evaluation.

[0014] A collaborative guidance method based on satellite on-orbit performance evaluation provided by the present invention includes:

[0015] Step S1: Collect the original data of the satellite and obtain the characteristic information of the observation area;

[0016] Step S2: Evaluate the observation performance of alternative target satellites for the observation area to obtain an observation performance report;

[0017] Step S3: Based on the observation performance report, transmit the guidance information to the target satellites that meet the requirements of the observation performance as needed.

[0018] Preferably, the original data includes: image data and echo data;

[0019] The observation area includes mountains, plains, and oceans; the characteristic information includes longitude, latitude, category, status, and signal strength;

[0020] In the step S1, preprocess the original data; the preprocessing includes: coordinate transformation, geometric correction, atmospheric correction, and radiation correction; for the radiation correction, convert the gray value of the original data into a radiation intensity value, and then confirm the signal strength of the observation area.

[0021] Preferably, in the step S2, it includes:

[0022] Step S2.1: Collect the performance indicators of the target satellite, the orbital information of the target satellite, the observation scene, and the information calculation model;

[0023] Step S2.2: Based on the longitude and latitude in the feature information of the observation area and the orbital information of the target satellite, calculate the observation field of view of the target satellite for the observation area, and determine whether the observation field of view can cover the target satellite in the observation area. If the result is yes, retain the target satellite; if the result is no, remove the target satellite;

[0024] Step S2.3: Based on the longitude, latitude, performance indicators of the target satellite, and the observation scenario in the feature information of the observation area, through the information calculation model, obtain the observation performance indicators of the target satellite for the observation area; the observation performance indicators of the target satellite for the observation area include the signal-to-clutter ratio;

[0025] Step S2.4: Output an observation performance report based on the observation performance indicators;

[0026] The performance indicators of the target satellite include satellite platform indicators, payload indicators, and on-board processing indicators;

[0027] The observation scenario includes: observation perspective, background environment, and atmospheric environment;

[0028] The orbital information includes: semi-major axis, eccentricity, orbital inclination, right ascension of the ascending node, argument of perigee, and true anomaly;

[0029] In the step S2.2, the process of obtaining the observation field of view of the target satellite for the observation area includes:

[0030] Step S2.2.1: Obtain satellite orbital information and observation field of view parameters;

[0031] Step S2.2.2: Based on the content obtained in step S2.2.1, calculate the observation width of the satellite;

[0032] Step S2.2.3: Based on the observation width, determine the coverage area of the satellite;

[0033] Step S2.2.4: Display the coverage area of the satellite through STK and generate a coverage report, and then determine whether the observation field of view can cover the target satellite in the observation area. If the result is yes, retain the target satellite; if the result is no, remove the target satellite;

[0034] The coverage report is a report showing the satellite coverage area;

[0035] The satellite orbital information includes: semi-major axis, eccentricity, orbital inclination, right ascension of the ascending node, argument of perigee, and true anomaly; the observation field of view parameter is the total field of view angle;

[0036] In the step S2.2.3, the mathematical expression of the observation width is:

[0037] Swa = 2×H×tan(2θ) (1)

[0038] Wherein, Swa represents the observation swath of the satellite; θ represents the total field of view angle; H represents the orbital altitude;

[0039] The coverage area includes the orbital coverage area and the observation field of view coverage area.

[0040] Preferably, in the step S2.3, the information calculation model includes: an observation area basic radiation model of surface reflection, an atmospheric transmission correction model, and an observation angle of view influence model;

[0041] In the step S2.3, based on the information calculation model, the process of calculating and obtaining the radiation intensity of the pixel points and then confirming the signal-to-noise ratio includes:

[0042] Step S2.3.1: Based on the observation area basic radiation model of surface reflection of the information calculation model, obtain the surface reflection radiance;

[0043] Step S2.3.2: Input the surface reflection radiance into the atmospheric transmission correction model of the information calculation model to obtain a radiation brightness correction result;

[0044] Step S2.3.3: Based on the radiation brightness correction result, according to the observation angle of view influence model of the information calculation model, obtain the radiation intensity received by the satellite sensor, that is, the radiation intensity of each pixel point;

[0045] Step S2.3.4: Based on the radiation intensity of each pixel point, statistically obtain the maximum radiation intensity at the center of the observation area, the mean value of the neighborhood background average radiation intensity, and the standard deviation of the neighborhood background spatial clutter radiation intensity, and then obtain the signal-to-noise ratio;

[0046] The mathematical expression of the observation area basic radiation model of surface reflection is:

[0047]

[0048] Wherein, Lsurface represents the surface reflection radiance, E0 is the solar irradiance at the top of the atmosphere, ρ is the surface reflectivity; θ s is the solar zenith angle, that is, the angle between the incident light and the surface normal; the symbol · represents multiplication;

[0049] The mathematical expression of the atmospheric transmission correction model is:

[0050] Ltotal = Lsurface·T + Lpath (3) Wherein, Ltotal represents the radiation luminance correction result, T represents the atmospheric transmittance; Lpath represents the atmospheric path radiation; The observation view angle influence model has the following mathematical expression:

[0051]

[0052] Wherein, I T represents the radiation intensity received by the satellite sensor; λ represents the effective band width of the sensor, λ1 represents the minimum value of the effective band width of the sensor; λ2 represents the maximum value of the effective band width of the sensor; f(θ v ) represents the response function;

[0053] Simplify formula (4) to confirm the radiation intensity of each pixel point. The mathematical expression is:

[0054]

[0055] Wherein, Δλ is the effective band width of the sensor;

[0056] The mathematical expression of the signal-to-clutter ratio is:

[0057]

[0058] Wherein, SCR represents the signal-to-clutter ratio, I Tmax represents the maximum radiation intensity at the center of the observation area, μ B represents the average radiation intensity mean value of the neighborhood background of the observation area, σ B represents the standard deviation of the clutter radiation intensity in the neighborhood background airspace;

[0059] In the step S3, based on the observation performance report, determine whether the observation performance index of the current target satellite is greater than or equal to a preset threshold as the observation threshold. If the result is yes, send the guidance information to the target satellite. If the result is no, do not process.

[0060] According to a collaborative guidance system based on satellite on-orbit performance evaluation provided by the present invention, it includes:

[0061] Module M1: Collect the original data of the satellite and obtain the characteristic information of the observation area;

[0062] Module M2: Evaluate the observation performance of alternative target satellites for the observation area to obtain an observation performance report;

[0063] Module M3: Based on the observation performance report, transmit the guidance information to the target satellite that meets the requirements of the observation performance as needed.

[0064] Preferably, the original data includes: image data and echo data;

[0065] The observation area includes mountains, plains and oceans; the characteristic information includes longitude, latitude, category, status and signal strength;

[0066] In the module M1, the original data is preprocessed; the preprocessing includes: coordinate transformation, geometric correction, atmospheric correction and radiation correction; the radiation correction is to convert the gray value of the original data into a radiation intensity value, and then confirm the signal strength of the observation area.

[0067] Preferably, in the module M2, it includes:

[0068] Module M2.1: Collect the performance indicators of the target satellite, the orbital information of the target satellite, the observation scene and the information calculation model;

[0069] Module M2.2: Based on the longitude and latitude in the characteristic information of the observation area and the orbital information of the target satellite, calculate the observation field of view of the target satellite for the observation area, and judge whether the observation field of view can cover the target satellite in the observation area. If the result is yes, keep the target satellite; if the result is no, remove the target satellite;

[0070] Module M2.3: Based on the longitude, latitude, the performance indicators of the target satellite and the observation scene in the characteristic information of the observation area, and processed by the information calculation model, obtain the observation performance indicators of the target satellite for the observation area; the observation performance indicators of the target satellite for the observation area include the signal-to-noise ratio;

[0071] Module M2.4: Output an observation performance report based on the observation performance indicators;

[0072] The performance indicators of the target satellite include satellite platform indicators, payload indicators and on-board processing indicators;

[0073] The observation scene includes: observation perspective, background environment and atmospheric environment;

[0074] The orbital information includes: semi-major axis, eccentricity, orbital inclination, right ascension of the ascending node, argument of perigee and true anomaly;

[0075] In the module M2.2, the process of obtaining the observation field of view of the target satellite for the observation area includes:

[0076] Module M2.2.1: Obtain satellite orbital information and observation field of view parameters;

[0077] Module M2.2.2: Calculate the observation width of the satellite based on the content obtained by the work of Module M2.2.1;

[0078] Module M2.2.3: Determine the coverage area of the satellite based on the observed wide swath;

[0079] Module M2.2.4: Display the coverage area of the satellite through STK and generate a coverage report, and then determine whether the observed field of view can cover the target satellite in the observation area. If the result is yes, retain the target satellite; if the result is no, remove the target satellite;

[0080] The coverage report is a report showing the satellite coverage area;

[0081] The satellite orbit information includes: semi-major axis, eccentricity, orbital inclination, right ascension of the ascending node, argument of perigee, and true anomaly; the observed field of view parameter is the total field of view angle;

[0082] In the module M2.2.3, the mathematical expression of the observed wide swath is:

[0083] Swa = 2×H×tan(2θ) (1)

[0084] Where, Swa represents the observed swath width of the satellite; θ represents the total field of view angle; H represents the orbital altitude;

[0085] The coverage area includes the orbit coverage area and the observed field of view coverage area.

[0086] Preferably, in the module M2.3, the information calculation model includes: the basic radiation model of the observed area reflected by the surface, the atmospheric transmission correction model, and the observation angle influence model;

[0087] In the module M2.3, based on the information calculation model, the process of calculating and obtaining the radiation intensity of the pixel points and then confirming the signal-to-noise ratio includes:

[0088] Module M2.3.1: Obtain the surface-reflected radiance based on the basic radiation model of the observed area reflected by the surface in the information calculation model;

[0089] Module M2.3.2: Input the surface-reflected radiance into the atmospheric transmission correction model of the information calculation model to obtain the radiation intensity correction result;

[0090] Module M2.3.3: Based on the radiation intensity correction result, obtain the radiation intensity received by the satellite sensor according to the observation angle influence model of the information calculation model, that is, the radiation intensity of each pixel point;

[0091] Module M2.3.4: Based on the radiation intensity of each pixel point, statistically obtain the maximum radiation intensity at the center of the observation area, the average radiation intensity mean of the neighborhood background, and the standard deviation of the clutter radiation intensity in the neighborhood background airspace, and then obtain the signal-to-noise ratio;

[0092] The mathematical expression of the observed regional basic radiation model of the surface reflection is as follows:

[0093]

[0094] Among them, Lsurface represents the surface reflection radiance, E0 is the solar irradiance at the top of the atmosphere, ρ is the surface reflectivity; θ s is the solar zenith angle, that is, the angle between the incident light and the surface normal; the symbol · represents multiplication;

[0095] The mathematical expression of the atmospheric transmission correction model is as follows:

[0096] Ltotal = Lsurface·T + LpatH (3) Among them, Ltotal represents the radiation brightness correction result, T represents the atmospheric transmittance; LpatH represents the atmospheric path radiation; the mathematical expression of the observation viewing angle influence model is as follows:

[0097]

[0098] Among them, I T represents the radiation intensity received by the satellite sensor; λ represents the effective band width of the sensor, λ1 represents the minimum value of the effective band width of the sensor; λ2 represents the maximum value of the effective band width of the sensor; f(θ v ) represents the response function;

[0099] Simplify formula (4) to confirm the radiation intensity of each pixel point. The mathematical expression is as follows:

[0100]

[0101] Among them, Δλ is the effective band width of the sensor;

[0102] The mathematical expression of the signal-to-clutter ratio is as follows:

[0103]

[0104] Among them, SCR represents the signal-to-clutter ratio, I Tmax represents the maximum radiation intensity at the center of the observed area, μ B represents the average radiation intensity mean of the neighborhood background of the observed area, σ B represents the standard deviation of the neighborhood background spatial clutter radiation intensity;

[0105] In the module M3, based on the observation performance report, judge whether the observation performance index of the current target satellite is greater than or equal to the preset threshold as the observation threshold. If the result is yes, send the guidance information to the target satellite. If the result is no, do not process.

[0106] A computer-readable storage medium storing a computer program, wherein when the computer program is executed by a processor, the steps of a collaborative guidance method for satellite on-orbit performance evaluation are implemented.

[0107] An electronic device provided according to the present invention includes a memory, a processor, and a computer program stored on the memory and executable on the processor. When the computer program is executed by the processor, the steps of a collaborative guidance method for satellite on-orbit performance evaluation are implemented.

[0108] Compared with the prior art, the present invention has the following beneficial effects:

[0109] 1. By performing further on-board processing on the original data, the present invention obtains richer characteristic information of the observation area.

[0110] 2. The present invention can comprehensively consider influencing factors such as satellite performance indicators, information calculation models, and observation scenarios, and then evaluate the observation performance of other satellites in real time, transmit guidance information as needed, and execute observation tasks, which helps to improve the utilization efficiency of the constellation.

[0111] 3. Based on the collaborative guidance method for satellite on-orbit performance evaluation, the present invention plans the observation tasks within the constellation, can obtain richer characteristic information of the observation area, and at the same time guides other satellites to execute observation tasks as needed, which can effectively avoid waste of observation resources and achieve an improvement in the overall utilization efficiency of the constellation.

[0112] 4. The present invention can combine information processing and analysis of the observation area, observation scenario constraints, and evaluation of satellite on-orbit observation performance to comprehensively guide the observation satellites in the constellation to execute the remote sensing observation process, which is expected to improve the overall utilization efficiency of the constellation. BRIEF DESCRIPTION OF THE DRAWINGS

[0113] By reading the following detailed description of non-limiting embodiments with reference to the accompanying drawings, other features, objects, and advantages of the present invention will become more apparent:

[0114] Figure 1 It is a schematic diagram of the work flow provided by the present invention;

[0115] Figure 2 It is a schematic diagram of the work based on a four-satellite constellation provided by the present invention. The satellites are respectively labeled as the home satellite, #1 other satellite, #2 other satellite, and #3 other satellite.

[0116] As shown in the figure:

[0117] Home satellite 101 #3 Other satellite 104

[0118] #1 Other satellite 102 Observation area 105

[0119] #2 Other satellite 103 Detailed implementation manners

[0120] The present invention will be described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that for those of ordinary skill in the art, without departing from the concept of the present invention, several changes and improvements can still be made. These all belong to the protection scope of the present invention.

[0121] In the present invention, before the satellite transmits collaborative guidance, the original data is pre-processed on the satellite, and then the guidance information is transmitted to other satellites as needed. The other satellites that receive the guidance information perform observation tasks.

[0122] As Figure 1 shown, a collaborative guidance method based on satellite on-orbit performance evaluation provided by the present invention includes:

[0123] Step S1: The satellite processes the original data to obtain the characteristic information of the observation area; the satellite herein refers to the satellite.

[0124] The characteristic information includes: the longitude and latitude, category, status, and signal strength of the observation area.

[0125] Step S2: The satellite evaluates the observation performance of alternative other satellites on the observation area; the other satellites herein refer to the target satellites.

[0126] Step S3: The satellite transmits the guidance information to the other satellites that meet the observation performance indicators as needed.

[0127] Step S4: The other satellites receive the guidance information and complete the observation tasks.

[0128] Specifically, the satellite processes the original data to obtain the characteristic information of the observation area including longitude and latitude, category, status, and signal strength. Specifically, in the method for evaluating the observation performance of alternative satellites, influencing factors such as the characteristics of the observation area, satellite performance indicators, information calculation models, and observation scenarios need to be comprehensively considered. The influencing factors of the satellite performance indicators include satellite platform indicators, payload indicators, and on-satellite processing indicators. The influencing factors of the information calculation models include observation area detection models, observation area positioning models, and time estimation models.

[0129] The influencing factors of the observation scenario include observation perspective, background environment, and atmospheric environment.

[0130] The satellite transmits the guidance information to the other satellites that meet the observation performance through an inter-satellite link, and the observation performance indicator can be set to 80%.

[0131] Specifically, the other satellites in the constellation that receive the guidance information perform the current observation task, and the remaining satellites can standby to receive other observation tasks.

[0132] Step S1: This satellite processes the raw data to obtain the feature information of the observation area.

[0133] In the step S1, the raw data processed by this satellite is the data of the observation area obtained by this satellite's observation, where the observation area includes mountains, plains, and oceans.

[0134] The raw data is the unprocessed data directly given by the satellite payload, including the image data obtained by the optical camera and the echo data obtained by the radar antenna.

[0135] This satellite further processes the initial data through on-board processing units to obtain more feature information of the observation area; the feature information includes: longitude and latitude, category, status, signal strength.

[0136] After receiving the raw data from the payload, the on-board processing unit performs the following steps to obtain the processed data and more abundant feature information such as longitude and latitude, category, status, signal strength, etc. The specific steps are as follows:

[0137] Step S1.1: Coordinate transformation, matching the raw data with the standard geographic coordinate system to obtain the geographical location, comparing it with the actual global location information database to determine the category of the observation area;

[0138] Step S1.2: Geometric correction, eliminating the influence of the earth's curvature on the data during sensor shooting, projecting the image onto a plane to obtain the true shape and size of the observation area;

[0139] Step S1.3: Atmospheric correction, using an atmospheric model to correct the raw data to eliminate the influence of atmospheric components and distance on the data radiation brightness value;

[0140] Step S1.4: Radiometric correction, converting the gray value of the raw data into a radiance value with physical meaning to determine the signal strength of the observation area;

[0141] Step S1.5: Determine the status of the observation area according to the recognition and detection algorithm of the observation area.

[0142] Step S2: This satellite evaluates the observation performance of alternative other satellites for the observation area.

[0143] In the step S2, the input parameters of the method for evaluating the observation performance of alternative satellites include the feature information of the observation area obtained by on-board processing in step S1 and influencing factors such as the orbit information of other satellites, the satellite performance indicators of other satellites, the information calculation model, and the observation scenario stored on this satellite.

[0144] The orbit information of other satellites is the orbit information of each satellite in the constellation.

[0145] The performance of the satellite, i.e., the performance indicators of the target satellite, includes: satellite platform indicators, payload indicators, and on-board processing indicators.

[0146] The information calculation model includes: the basic radiation model of the observed area reflected by the earth's surface, the atmospheric transmission correction model, and the observation angle influence model.

[0147] The observation scenario includes: observation angle, background environment, and atmospheric environment.

[0148] The orbital information includes: semi-major axis, eccentricity, orbital inclination, right ascension of the ascending node, argument of perigee, and true anomaly.

[0149] The present invention provides the observation performance of other satellites alternative to the evaluation of the present satellite for the observed area. The process of its software system includes:

[0150] Step S2.1: Let the present satellite, i.e., the satellite, collect the characteristic information of the observed area, the satellite performance indicators of other satellites, the information calculation model, the observation scenario, etc. as input parameters;

[0151] In other words, Step S2.1: Collect the observation performance indicators of the target satellite, the orbital information of the target satellite, the observation scenario, and the information calculation model;

[0152] Step S2.2: Based on the longitude and latitude information of the observed area and the orbital information of other satellites, calculate the observation field of view of other satellites for the observed area, and screen and remove other satellites whose observation field of view cannot cover the observed area;

[0153] Step S2.3: Based on the longitude and latitude of the observed area, the satellite performance indicators of other satellites, and the observation scenario, through the processing of the information calculation model, obtain the observation performance indicators of other satellites for the observed area, such as the signal-to-noise ratio;

[0154] Step S2.4: Integrate to obtain the observation performance indicators of other satellites for the observed area, output the observation performance parameters / reports, and complete the evaluation task of the present satellite.

[0155] Specifically, in Step S2.2, the process of obtaining the observation field of view of other satellites, i.e., the target satellite, for the observed area includes:

[0156] Step S2.2.1: Obtain the satellite orbital information and the observation field of view parameters;

[0157] The satellite orbital information includes: semi-major axis, eccentricity, orbital inclination, right ascension of the ascending node, argument of perigee, and true anomaly. The observation field of view parameter is the total field of view angle, which is used to calculate the width of the satellite, i.e., the observation width.

[0158] Step S2.2.2 Calculate the width of the satellite;

[0159] According to the orbital altitude and the total field of view angle, calculate the observation swath width of the satellite. The mathematical expression is as follows:

[0160] Swa = 2×H×tan(2θ) (1)

[0161] Wherein, Swa represents the observation swath width of the satellite; θ represents the total field of view angle; H represents the orbital altitude;

[0162] Step S2.2.3: Determine the coverage area of the satellite;

[0163] The orbital coverage area, that is, the orbital altitude and inclination angle of the satellite determine the scope of its coverage area.

[0164] The observation field of view coverage area, by combining the swath width and the orbital trajectory of the satellite, can determine the coverage area of the satellite at a certain moment.

[0165] Step S2.2.4: Use professional software for analysis;

[0166] The professional software is STK, the full name is Satellite Tool Kit;

[0167] Import the satellite orbit data, create satellite and ground target objects through STK, run the coverage analysis module of STK, display the coverage area of the satellite, and generate a coverage report. The coverage report is a report showing the coverage area of the satellite;

[0168] In the step S2.2.4, the process of displaying the coverage area of the satellite based on STK includes:

[0169] Step S2.2.4.1: Create a satellite object and input orbital parameters;

[0170] Step S2.2.4.2: Create a ground target object and set the longitude and latitude of the target location;

[0171] Step S2.2.4.3: Run the coverage analysis, and set the analysis time range and step size according to the task requirements;

[0172] Step S2.2.4.4: View the coverage result, judge whether the target location is within the observation field of view of the satellite. If the result is yes, do not process. If the result is no, remove other satellites whose observation fields of view cannot cover the observation area;

[0173] Specifically, in the step S2.3, taking the calculation model of the visible light radiation information of the satellite observing the earth's surface as an example, the process of calculating the radiation intensity of each pixel point includes:

[0174] Step S2.3.1: The basic radiation model of the observation area reflected by the earth's surface;

[0175] The mathematical expression for the surface reflected radiance of the basic radiation model in the observation area is as follows:

[0176]

[0177] Among them, Lsurface represents the surface reflected radiance, E0 is the solar irradiance at the top of the atmosphere, with the unit of W / m 2 ·μm; ρ is the surface reflectivity; θ s is the solar zenith angle, that is, the angle between the incident light and the surface normal; the symbol · represents multiplication;

[0178] Step S2.3.2: Atmospheric transmission correction model;

[0179] The surface radiation needs to pass through atmospheric attenuation and scattering to reach the satellite sensor, and the radiance is corrected as:

[0180] Ltotal = Lsurface·T + Lpat (3)

[0181] The atmospheric transmittance, that is, T, includes the direct transmittance Tdirect and the diffuse transmittance Tdiffuse; the atmospheric transmittance is related to the atmospheric optical thickness and the satellite observation zenith angle.

[0182] The path radiance of the atmosphere, that is, Lpath, is generated by atmospheric scattering and is related to the solar zenith angle θ s and the satellite observation zenith angle θ v , that is, the angle between the satellite observation direction and the surface normal and the atmospheric parameters.

[0183] The atmospheric scattering includes: Rayleigh scattering, aerosol scattering;

[0184] Step S2.3.3 Observation angle influence model;

[0185] The radiation intensity received by the satellite sensor is related to the sensor field of view angle and the response function, that is, f(θ v ), and the mathematical expression is:

[0186]

[0187] Among them, the integration range [λ1, λ2] is determined by the spectral response characteristics of the sensor; I T represents the radiation intensity received by the satellite sensor; λ represents the effective band width of the sensor, λ1 represents the minimum value of the effective band width of the sensor; λ2 represents the maximum value of the effective band width of the sensor; f(θ v ) represents the response function;

[0188] The response function takes into account the influence of the sensor field of view angle on the effective receiving area and is inversely proportional to cosθ v .

[0189] Step S2.3.4: Final radiation model

[0190] For the radiation model, ignoring multiple scattering and aerosol polarization effects, the simplified formula for the radiation intensity of each pixel point finally is as follows:

[0191]

[0192] where Δλ is the effective band width of the sensor.

[0193] Specifically, in step S2.3, according to steps S2.3.1 to S2.3.4, the radiation intensity of each pixel in the observation area is calculated, and the maximum radiation intensity at the center of the observation area, the mean value of the neighborhood background average radiation intensity, and the standard deviation of the neighborhood background spatial clutter radiation intensity are statistically obtained.

[0194] Therefore, the signal-to-clutter ratio can be calculated by the ratio of the absolute value of the difference between the maximum radiation intensity at the center of the observation area and the mean value of the neighborhood background average radiation intensity to the standard deviation of the neighborhood background spatial clutter radiation intensity, as shown in formula (1).

[0195] The mathematical expression of the signal-to-clutter ratio is as follows:

[0196]

[0197] where SCR represents the signal-to-clutter ratio, I Tmax represents the maximum radiation intensity at the center of the observation area, μ B represents the mean value of the neighborhood background average radiation intensity of the observation area, and σ B represents the standard deviation of the neighborhood background spatial clutter radiation intensity.

[0198] Step S3: This satellite transmits the guidance information to other satellites that meet the observation performance indicators as required.

[0199] The observation performance of the other satellites is obtained by the on-satellite evaluation of this satellite in step S2.

[0200] The guidance information is transmitted by this satellite to other satellites that meet the observation performance through the inter-satellite link. The inter-satellite link includes microwave links in frequency bands such as Ka / Q / V / W and laser links with wavelengths such as 800nm / 1064nm / 1550nm.

[0201] The indicators that meet the observation performance can be set as required, such as being set to 80%.

[0202] The on-demand allocation according to the observation performance is specifically implemented as follows: According to the observation task and the unified observation threshold, it is judged whether the observation performance value of the current other satellite is greater than or equal to the observation threshold. If the result is yes, the guidance information is sent to the other satellite; if the result is no, it is not processed.

[0203] S4: Other satellites receive the guiding information and complete the observation tasks.

[0204] Among the satellites in the constellation, the other satellites that meet the observation performance indicators will receive the guiding information transmitted by this satellite and execute the current observation tasks. The other satellites that do not meet the observation performance indicators of the current observation tasks will not receive the guiding information transmitted by this satellite, do not participate in the current observation tasks, and can standby to receive other observation tasks.

[0205] See Figure 2 As shown, in this embodiment, taking a small constellation composed of 4 satellites as an example, a schematic diagram of a typical scenario of the collaborative guiding method based on on-orbit performance evaluation is given.

[0206] The small constellation in the typical scenario includes this satellite 101, #1 other satellite 102, #2 other satellite 103, and #3 other satellite 104. There is also an observation area 105 in the typical scenario.

[0207] This satellite 101 first performs on-board processing on the initial data of the observation area 105 obtained by observing this satellite 101, and further obtains the characteristic information of the observation area, including longitude and latitude, category, status, and signal strength.

[0208] This satellite 101 combines the characteristic information of the observation area 105 obtained by on-board processing and the influencing factors such as the satellite performance indicators, information calculation models, and observation scenarios of #1 other satellite 102, #2 other satellite 103, and #3 other satellite 104 stored on board this satellite 101 to evaluate the observation fields of view and observation performances of the alternative #1 other satellite 102, #2 other satellite 103, and #3 other satellite 104 for the observation area 105.

[0209] Due to the reason of the observation field of view, the observation field of view of #2 other satellite 103 cannot cover the observation area and does not participate in the current task.

[0210] Due to the reason of the payload characteristics, the performance indicators of #1 other satellite 102 evaluated by this satellite 101 are 48%, the performance indicators of #2 other satellite 103 are 75%, and the performance indicators of #3 other satellite 104 are 93%. The observation performance indicators set by this satellite 101 are 80%. Therefore, only #3 other satellite 104 meets the observation performance indicators.

[0211] This satellite 101 transmits the guiding information only to #3 other satellite 104.

[0212] #3 other satellite 104 receives the guiding information transmitted by this satellite 101 and executes the collaborative observation task. #1 other satellite 102 and #2 other satellite 103 do not meet the observation fields of view and observation performance indicators of the current observation tasks and will not receive the guiding information transmitted by this satellite 101, and can standby to receive other observation tasks.

[0213] The present invention also provides a collaborative guidance system based on satellite on-orbit performance evaluation. The collaborative guidance system based on satellite on-orbit performance evaluation can be implemented by executing the process steps of the collaborative guidance method based on satellite on-orbit performance evaluation. That is, those skilled in the art can understand the collaborative guidance method based on satellite on-orbit performance evaluation as a preferred implementation manner of the collaborative guidance system based on satellite on-orbit performance evaluation.

[0214] A collaborative guidance system based on satellite on-orbit performance evaluation provided by the present invention includes:

[0215] Module M1: Collect the original data of the satellite and obtain the characteristic information of the observation area;

[0216] Module M2: Evaluate the observation performance of alternative target satellites for the observation area and obtain an observation performance report;

[0217] Module M3: Based on the observation performance report, transmit the guidance information to the target satellites that meet the requirements of the observation performance as needed.

[0218] Those skilled in the art know that in addition to implementing the system and its various devices, modules, and units provided by the present invention in the form of pure computer-readable program code, the method steps can be logically programmed to enable the system and its various devices, modules, and units provided by the present invention to be implemented in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers to achieve the same functions. Therefore, the system and its various devices, modules, and units provided by the present invention can be regarded as a hardware component, and the devices, modules, and units included therein for implementing various functions can also be regarded as the structures within the hardware component; the devices, modules, and units for implementing various functions can also be regarded as either software modules for implementing the method or structures within the hardware component.

[0219] The specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Without conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A collaborative guidance method based on satellite on-orbit performance evaluation, characterized in that: include: Step S1: Collecting raw data from the satellite to obtain characteristic information of the observation area; Step S2: evaluating the observation performance of the candidate target satellite over the observation area to obtain an observation performance report; Step S3: Based on the observation performance report, the guidance information is transmitted as needed to the target satellite that meets the observation performance requirements.

2. The collaborative guidance method based on satellite on-orbit performance evaluation according to claim 1 is characterized in that: The original data includes: image data and echo data; The observation area includes mountains, plains and oceans; the characteristic information includes longitude, latitude, category, status and signal strength; In the step S1, the raw data is preprocessed; the preprocessing includes: coordinate conversion, geometric correction, atmospheric correction and radiation correction; the radiation correction is to convert the grayscale value of the raw data into a radiation intensity value, thereby confirming the signal intensity of the observation area.

3. The collaborative guidance method based on satellite on-orbit performance evaluation according to claim 2 is characterized in that: In the step S2, it includes: Step S2.1: Collect the observation performance index of the target satellite, the orbit information of the target satellite, the observation scene and the information calculation model; Step S2.2: Based on the longitude and latitude in the characteristic information of the observation area and the orbit information of the target satellite, the observation field of view of the target satellite over the observation area is calculated, and it is determined whether the observation field of view can cover the target satellite in the observation area. If the result is yes, the target satellite is retained, and if the result is no, the target satellite is removed; Step S2.3: Based on the longitude, latitude, performance index of the target satellite and observation scene in the characteristic information of the observation area, the observation performance index of the target satellite for the observation area is obtained through information calculation model processing; the observation performance index of the target satellite for the observation area includes a signal-to-noise ratio; Step S2.4: outputting an observation performance report based on the observation performance indicator; The performance indicators of the target satellite include satellite platform indicators, payload indicators and on-board processing indicators; The observation scene includes: observation perspective, background environment and atmospheric environment; The orbit information includes: semi-major axis, eccentricity, orbit inclination, right ascension of ascending node, argument of perigee and true anomaly; In step S2.2, the process of obtaining the observation field of view of the target satellite on the observation area includes: Step S2.2.1: Obtain satellite orbit information and observation field parameters; Step S2.2.2: Based on the content obtained in step S2.2.1, calculate the observation width of the satellite; Step S2.2.3: Determine the coverage area of ​​the satellite based on the observation width; Step S2.2.4: Display the satellite coverage area through STK and generate a coverage report, and then determine whether the observation field of view can cover the target satellite in the observation area. If the result is yes, retain the target satellite, and if the result is no, remove the target satellite; The coverage report is a report showing the satellite coverage area; The satellite orbit information includes: semi-major axis, eccentricity, orbit inclination, right ascension of ascending node, argument of perigee and true anomaly; the observation field of view parameter is the total field of view angle; In step S2.2.3, the mathematical expression of the observation width is: Swa=2×H×tan(2θ) (1) Among them, Swa represents the observation width of the satellite; θ represents the total field of view; H represents the orbital height; The coverage area includes a track coverage area and an observation field coverage area.

4. The collaborative guidance method based on satellite on-orbit performance evaluation according to claim 3 is characterized in that: In step S2.3, the information calculation model includes: a basic radiation model of the observation area of ​​surface reflection, an atmospheric transmission correction model and an observation viewing angle influence model; In step S2.3, the process of calculating and obtaining the radiation intensity of the pixel point based on the information calculation model, and then confirming the signal-to-noise ratio includes: Step S2.3.1: Obtain the surface reflected radiation brightness based on the basic radiation model of the observation area of ​​the surface reflection of the information calculation model; Step S2.3.2: Input the surface reflected radiation brightness into the atmospheric transmission correction model of the information calculation model to obtain the radiation brightness correction result; Step S2.3.3: Based on the radiation brightness correction result, according to the observation angle influence model of the information calculation model, the radiation intensity received by the satellite sensor, that is, the radiation intensity of each pixel point, is obtained; Step S2.3.4: Based on the radiation intensity of each pixel point, the maximum radiation intensity at the center of the observation area, the mean value of the average radiation intensity of the neighborhood background and the standard deviation of the radiation intensity of the clutter in the neighborhood background space are counted and obtained, thereby obtaining the signal-to-noise ratio; The mathematical expression of the basic radiation model of the observation area reflected by the surface is: Where Lsurface represents the surface reflected radiation brightness, E0 is the solar irradiance at the top of the atmosphere, ρ is the surface reflectivity; θ s is the solar zenith angle, i.e. the angle between the incident light and the surface normal; the symbol · indicates multiplication; The mathematical expression of the atmospheric transmission correction model is: Ltotal=Lsurface·T+Lpath (3) Among them, Ltotal represents the radiation brightness correction result, T represents the atmospheric transmittance; Lpath represents the atmospheric path radiation; The observation perspective affects the model, and the mathematical expression is: Among them, I T represents the radiation intensity received by the satellite sensor; λ represents the effective band width of the sensor, λ1 represents the minimum value of the effective band width of the sensor; λ2 represents the maximum value of the effective band width of the sensor; f(θ v ) represents the response function; Simplify formula (4) to determine the radiation intensity of each pixel. The mathematical expression is: Among them, Δλ is the effective band width of the sensor; The mathematical expression of the signal-to-noise ratio is: Among them, SCR represents the signal-to-noise ratio, I Tmax Indicates the maximum radiation intensity at the center of the observation area, μ B represents the mean value of the average background radiation intensity in the neighborhood of the observation area, σ B Represents the standard deviation of the clutter radiation intensity in the neighborhood background space; In step S3, based on the observation performance report, it is determined whether the observation performance index of the current target satellite is greater than or equal to a preset threshold value as an observation threshold. If the result is yes, guidance information is sent to the target satellite. If the result is no, no processing is performed.

5. A collaborative guidance system based on satellite on-orbit performance evaluation, characterized in that: include: Module M1: collects raw data from satellites and obtains characteristic information of the observation area; Module M2: Evaluate the observation performance of the candidate target satellite over the observation area and obtain an observation performance report; Module M3: Based on the observation performance report, the guidance information is transmitted as needed to the target satellite that meets the observation performance requirements.

6. The collaborative guidance system based on satellite on-orbit performance evaluation according to claim 5, characterized in that: The original data includes: image data and echo data; The observation area includes mountains, plains and oceans; the characteristic information includes longitude, latitude, category, status and signal strength; In the module M1, the raw data is preprocessed; the preprocessing includes: coordinate conversion, geometric correction, atmospheric correction and radiation correction; the radiation correction is to convert the grayscale value of the raw data into a radiation intensity value, thereby confirming the signal intensity of the observation area.

7. The collaborative guidance system for satellite on-orbit performance evaluation according to claim 6, characterized in that: The module M2 includes: Module M2.1: Collect the observation performance indicators of the target satellite, the orbit information of the target satellite, the observation scene and the information calculation model; Module M2.2: Based on the longitude and latitude in the characteristic information of the observation area and the orbit information of the target satellite, calculate the observation field of view of the target satellite over the observation area, and judge whether the observation field can cover the target satellite in the observation area. If the result is yes, retain the target satellite, otherwise, remove the target satellite; Module M2.3: Based on the longitude, latitude, performance index of the target satellite and the observation scene in the characteristic information of the observation area, the observation performance index of the target satellite for the observation area is obtained through information calculation model processing; the observation performance index of the target satellite for the observation area includes a signal-to-noise ratio; Module M2.4: outputting an observation performance report based on the observation performance indicator; The performance indicators of the target satellite include satellite platform indicators, payload indicators and on-board processing indicators; The observation scene includes: observation perspective, background environment and atmospheric environment; The orbit information includes: semi-major axis, eccentricity, orbit inclination, right ascension of ascending node, argument of perigee and true anomaly; In the module M2.2, the process of obtaining the observation field of the target satellite on the observation area includes: Module M2.2.1: Obtain satellite orbit information and observation field parameters; Module M2.2.2: Based on the content obtained from the work of Module M2.2.1, calculate the observation width of the satellite; Module M2.2.3: Determine the coverage area of ​​the satellite based on the observation width; Module M2.2.4: Display the satellite coverage area through STK and generate a coverage report, and then determine whether the observation field of view can cover the target satellite in the observation area. If the result is yes, the target satellite is retained, and if the result is no, the target satellite is removed; The coverage report is a report showing the satellite coverage area; The satellite orbit information includes: semi-major axis, eccentricity, orbit inclination, right ascension of ascending node, argument of perigee and true anomaly; the observation field of view parameter is the total field of view angle; In the module M2.2.3, the mathematical expression of the observation width is: Swa=2×H×tan(2θ) (1) Among them, Swa represents the observation width of the satellite; θ represents the total field of view; H represents the orbital height; The coverage area includes a track coverage area and an observation field coverage area.

8. The collaborative guidance system for satellite on-orbit performance evaluation according to claim 7, characterized in that: In the module M2.3, the information calculation model includes: a basic radiation model of the observation area of ​​surface reflection, an atmospheric transmission correction model and an observation viewing angle influence model; In the module M2.3, based on the information calculation model, the radiation intensity of the pixel point is calculated and obtained, and then the process of confirming the signal-to-noise ratio includes: Module M2.3.1: Basic radiation model of the observation area based on the surface reflection of the information calculation model to obtain the surface reflection radiation brightness; Module M2.3.2: Input the surface reflected radiation brightness into the atmospheric transmission correction model of the information calculation model to obtain the radiation brightness correction result; Module M2.3.3: Based on the radiation brightness correction result, the radiation intensity received by the satellite sensor, that is, the radiation intensity of each pixel point, is obtained according to the observation perspective influence model of the information calculation model; Module M2.3.4: Based on the radiation intensity of each pixel point, the maximum radiation intensity at the center of the observation area, the mean value of the average radiation intensity of the neighborhood background and the standard deviation of the radiation intensity of the clutter in the neighborhood background space are counted and obtained, thereby obtaining the signal-to-noise ratio; The mathematical expression of the basic radiation model of the observation area reflected by the surface is: Where Lsurface represents the surface reflected radiation brightness, E0 is the solar irradiance at the top of the atmosphere, ρ is the surface reflectivity; θ s is the solar zenith angle, i.e. the angle between the incident light and the surface normal; the symbol · indicates multiplication; The mathematical expression of the atmospheric transmission correction model is: Ltotal=Lsurface·T+Lpath (3) Among them, Ltotal represents the radiation brightness correction result, T represents the atmospheric transmittance; Lpath represents the atmospheric path radiation; The observation perspective affects the model, and the mathematical expression is: Among them, I T represents the radiation intensity received by the satellite sensor; λ represents the effective band width of the sensor, λ1 represents the minimum value of the effective band width of the sensor; λ2 represents the maximum value of the effective band width of the sensor; f(θ v ) represents the response function; Simplify formula (4) to determine the radiation intensity of each pixel. The mathematical expression is: Among them, Δλ is the effective band width of the sensor; The mathematical expression of the signal-to-noise ratio is: Among them, SCR represents the signal-to-noise ratio, I Tmax Indicates the maximum radiation intensity at the center of the observation area, μ B represents the mean value of the average background radiation intensity in the neighborhood of the observation area, σ B Represents the standard deviation of the clutter radiation intensity in the neighborhood background space; In the module M3, based on the observation performance report, it is determined whether the observation performance index of the current target satellite is greater than or equal to a preset threshold value as an observation threshold. If the result is yes, the guidance information is sent to the target satellite. If the result is no, no processing is performed.

9. A computer-readable storage medium storing a computer program, characterized in that: When the computer program is executed by a processor, the steps of the collaborative guidance method for on-orbit performance evaluation of a satellite according to any one of claims 1 to 4 are implemented.

10. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein: When the computer program is executed by a processor, the steps of the collaborative guidance method for on-orbit performance evaluation of a satellite according to any one of claims 1 to 4 are implemented.

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