Constellation forming method and system for north-south collaborative detection of active remote sensing satellite system

Abstract

The application provides a constellation forming method and system for north-south cooperative detection of an active remote sensing satellite system, comprising the following steps: using the detection capability of an active remote sensing load, combining the latitude range requirement of detection, selecting an orbit height and an inclination, and proposing a special constellation configuration, so that the north-south detectable ranges of multiple satellites are spliced, the quasi-simultaneous cooperative detection of a large-scale area in the north-south direction is realized, the advantages of the active remote sensing satellite, such as a large field of view and flexible detection range, are fully exerted, the algorithm is reliable and stable, the general range is wide, the applicability is strong, and the application prospect and market prospect are good.

Description

Technical Field

[0001] This invention relates to the field of satellite overall design, and more specifically, to a constellation formation method and system for north-south collaborative detection of active remote sensing satellite systems in the field of on-orbit application mode performance optimization design. Background Technology

[0002] Active remote sensing satellites have advantages such as a large field of view and flexible detection range. Multiple active remote sensing satellite systems can combine the advantages of the field of view and give full play to the characteristics of the north-south combined motion of the constellation to achieve large-scale collaborative detection in the north-south direction.

[0003] Patent document CN106156417A provides a method for optimizing the configuration of a satellite constellation for rapid revisiting at equal time intervals. This method aims to achieve rapid revisiting of the mission target at equal time intervals. It adopts a low-inclination regression Walker constellation as the basic configuration and uses indicators such as the number of satellites, orbital altitude, revisit time interval, coverage characteristics, maneuverability, and optical imaging performance of a single satellite as optimization constraints. Based on a multi-island genetic algorithm, it achieves rapid revisiting of the specified target at equal time intervals with fewer satellites.

[0004] However, the constellation design scheme in patent document CN106156417A aims to optimize revisit time to achieve rapid revisit of mission targets at equal time intervals, which cannot adapt to the constellation design for north-south cooperative exploration.

[0005] Patent document CN106249253A provides an optimization design method for a hybrid constellation of low-Earth orbit communication and navigation enhancement, including: determining the satellite orbit type; determining the satellite orbit altitude; determining the minimum observation elevation angle; selecting the constellation configuration; determining the orbit inclination angle; determining the number of satellites; determining the number of orbital planes and phase factors; optimizing the selection of the initial ascending node right ascension; analyzing the coverage performance of the hybrid constellation of low-Earth orbit communication and navigation enhancement; and comparing all hybrid constellation parameters that meet the design requirements after traversal, and selecting the optimal solution.

[0006] However, a shortcoming of patent document CN106249253A is that it does not describe how to select the number of orbital planes and the range of phase factors that provide optimal coverage performance. Summary of the Invention

[0007] To address the shortcomings of existing technologies, the purpose of this invention is to provide a constellation formation method and system for north-south coordinated detection by an active remote sensing satellite system.

[0008] A constellation formation method for north-south coordinated detection of an active remote sensing satellite system according to the present invention includes:

[0009] Step SA: Based on the payload detection capabilities of the active remote sensing satellite and the required latitudinal range for detection, select the orbital altitude and orbital inclination.

[0010] Step SB: Based on the orbital altitude and orbital inclination, obtain the constellation scheme of the active remote sensing satellite system, so that the north-south detectable range of multiple satellites can be stitched together.

[0011] Preferably, step SA includes:

[0012] Step S1: Determine the orbital altitude based on the payload detection capabilities of the active remote sensing satellite;

[0013] Step S2: Determine the orbital inclination angle based on the latitude range and orbital altitude of the north-south exploration area;

[0014] Step S3: Determine the number of satellite orbital planes based on the satellite payload's detection capabilities;

[0015] Step S4: Adjust the orbital inclination angle according to the constellation and satellite payload detection capabilities to maximize the detection latitude range.

[0016] Preferably, in step S1, the load detection capability includes the furthest operating distance. According to the farthest effective distance Obtain the orbital height :

[0017]

[0018] in, The radius of the Earth;

[0019] In step S2, the latitudinal range of the north-south detection area is the maximum value of the south and north latitudes of interest. Track inclination Calculated by the following formula:

[0020]

[0021] in The geocentric angle from the farthest point on the ground to the sub-satellite point is calculated by the following formula:

[0022]

[0023] in The maximum angle of incidence in the field of view that the payload can detect;

[0024] In step S3, the payload detection capability includes the geocentric angle from the payload's farthest point on the ground to the nadir point. and the geocentric angle of the ground detectable range of the load , Calculated by the following formula:

[0025]

[0026] in The minimum incident angle of the field of view that the payload can detect;

[0027] Number of orbital surfaces This refers to the number of satellites in a north-south oriented group, calculated using the following formula:

[0028]

[0029] The function ceil returns the smallest integer that is greater than or equal to the specified expression;

[0030] In step S4, the orbital inclination is adjusted according to the actual overlap between the constellation and the payload's detection capabilities to maximize the detection latitude range.

[0031] Preferably, step SB includes:

[0032] Step S5: Calculate the orbital return period based on the orbital height range and the orbital inclination angle;

[0033] Step S6: Based on the revisit requirements of the probe and the orbital return period, determine the number of satellites in each satellite orbital plane to obtain the total number of satellites;

[0034] Step S7: Select the constellation relative phase angle parameters according to the number of satellites;

[0035] Step S8: Calculate the relative phase angle value of the constellation based on the constellation relative phase angle parameters; finally, give the constellation scheme of the active remote sensing satellite system.

[0036] Preferably, in step S5, the orbital return period Calculated by the following formula:

[0037]

[0038] in, The gravitational constant of Earth;

[0039] In step S6, the number of satellites in each orbital plane Calculated by the following formula:

[0040]

[0041] in To meet the revisit requirement of the probe;

[0042] number of satellites Calculated by the following formula:

[0043]

[0044] In step S7, the constellation relative phase angle parameter is the constellation phase angle difference parameter F of the first satellite in the adjacent orbit;

[0045] In step S8, the relative phase angle value of the constellation is the phase angle difference between the first satellite in the adjacent orbit. The specific settings for the satellite orbit are calculated using the following formula:

[0046]

[0047] The constellation scheme of the active remote sensing satellite system is described by the parameters of orbital altitude, orbital inclination, number of orbital planes, number of satellites per orbital plane, and relative phase angle of the constellation.

[0048] According to the present invention, a constellation formation system for north-south coordinated detection of an active remote sensing satellite system includes:

[0049] Module MA: Based on the payload detection capabilities of the active remote sensing satellite and the required latitudinal range for detection, select the orbital altitude and orbital inclination.

[0050] Module MB: Based on the orbital altitude and orbital inclination, a constellation scheme for the active remote sensing satellite system is obtained, which allows the north-south detectable range of multiple satellites to be stitched together.

[0051] Preferably, the module MA includes:

[0052] Module M1: Determines the orbital altitude based on the payload detection capabilities of the active remote sensing satellite;

[0053] Module M2: Determines the orbital inclination angle based on the latitude range and orbital altitude of the north-south exploration area;

[0054] Module M3: Determines the number of satellite orbital planes based on the satellite payload's detection capabilities;

[0055] Module M4: Adjusts the orbital inclination based on the constellation and satellite payload detection capabilities to maximize the detection latitude range.

[0056] Preferably, in module M1, the load detection capability includes the furthest operating distance. According to the farthest effective distance Obtain the orbital height :

[0057]

[0058] in, The radius of the Earth;

[0059] In module M2, the latitude range of the north-south detection area is the maximum value of the south and north latitudes of interest. Track inclination Calculated by the following formula:

[0060]

[0061] in The geocentric angle from the farthest point on the ground to the sub-satellite point is calculated by the following formula:

[0062]

[0063] in The maximum angle of incidence in the field of view that the payload can detect;

[0064] In module M3, the payload detection capability includes the geocentric angle from the payload's farthest point on the ground to the nadir point. and the geocentric angle of the ground detectable range of the load , Calculated by the following formula:

[0065]

[0066] in The minimum incident angle of the field of view that the payload can detect;

[0067] Number of orbital surfaces This refers to the number of satellites in a north-south oriented group, calculated using the following formula:

[0068]

[0069] The function ceil returns the smallest integer that is greater than or equal to the specified expression;

[0070] In module M4, the orbital inclination is adjusted according to the actual overlap between the constellation and the payload's detection capabilities to maximize the detection latitude range.

[0071] Preferably, the module MB includes:

[0072] Module M5: Calculates the orbital return period based on the orbital height range and the orbital inclination angle;

[0073] Module M6: Based on the revisit requirements of the probe and the orbital return period, determine the number of satellites in each satellite orbital plane to obtain the total number of satellites;

[0074] Module M7: Selects the constellation relative phase angle parameters based on the number of satellites;

[0075] Module M8: Calculates the relative phase angle value of the constellation based on the constellation relative phase angle parameters; and finally provides a constellation scheme for the active remote sensing satellite system.

[0076] Preferably, in module M5, the orbital return period Calculated by the following formula:

[0077]

[0078] in, The gravitational constant of Earth;

[0079] In module M6, the number of satellites per orbital plane Calculated by the following formula:

[0080]

[0081] in To meet the revisit requirement of the probe;

[0082] number of satellites Calculated by the following formula:

[0083]

[0084] In module M7, the constellation relative phase angle parameter is the constellation phase angle difference parameter F of the first satellite in the adjacent orbit;

[0085] In module M8, the relative phase angle value of the constellation is the phase angle difference between the first satellite in the adjacent orbit. The specific settings for the satellite orbit are calculated using the following formula:

[0086]

[0087] The constellation scheme of the active remote sensing satellite system is described by the parameters of orbital altitude, orbital inclination, number of orbital planes, number of satellites per orbital plane, and relative phase angle of the constellation.

[0088] Compared with the prior art, the present invention has the following beneficial effects:

[0089] 1. In the constellation scheme of this invention, active remote sensing satellites are used, which have advantages such as a large field of view and flexible detection range. The combination of multiple active remote sensing satellite systems with the advantages of the field of view fully utilizes the characteristics of the north-south combined motion of the constellation, and can realize large-scale collaborative detection in the north-south direction.

[0090] 2. This invention addresses the needs of satellites with large field of view, large detection area, and north-south distribution, while requiring near-simultaneous detection of the detection area. It proposes an improved constellation scheme that allows the north-south detection range of multiple satellites to be stitched together.

[0091] 3. The algorithm of this invention is reliable and stable, has a wide range of applications, strong applicability, and good application and market prospects. Attached Figure Description

[0092] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0093] Figure 1 This is the process for designing the constellation for north-south coordinated detection of the active remote sensing satellite system of the present invention.

[0094] Figure 2 This is a schematic diagram illustrating the relationship between the active remote sensing satellite detection range of this invention and the Earth.

[0095] Figure 3 This is a schematic diagram of the north-south coordinated combination of the detection range of the active remote sensing satellite system of the present invention. Detailed Implementation

[0096] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0097] This invention presents a constellation formation method for north-south coordinated detection of an active remote sensing satellite system. Utilizing the detection capabilities of the active remote sensing payload and considering the required latitudinal range, it selects the orbital altitude and inclination, and proposes a constellation configuration that stitches together the north-south detectable ranges of multiple satellites, achieving near-simultaneous coordinated detection of a large north-south area. In other words, this invention specifically addresses the characteristics of remote sensing payloads and their unique coverage requirements, providing a targeted method for selecting the Walker constellation.

[0098] This invention provides a constellation formation method for north-south coordinated detection of an active remote sensing satellite system, comprising the following steps:

[0099] Step S1: Determine the orbital altitude based on the payload detection capabilities of the active remote sensing satellite;

[0100] Step S2: Determine the orbital inclination angle based on the latitude range and orbital altitude of the north-south exploration area;

[0101] Step S3: Determine the number of satellite orbital planes based on the satellite payload's detection capabilities;

[0102] Step S4: Adjust the orbital inclination angle according to the constellation and satellite payload detection capabilities to maximize the detection latitude range;

[0103] Step S5: Calculate the orbital return period based on the orbital height range and the orbital inclination angle;

[0104] Step S6: Based on the revisit requirements of the probe and the orbital return period, determine the number of satellites in each satellite orbital plane to obtain the total number of satellites;

[0105] Step S7: Optimize the relative phase angle parameters of the constellation based on the number of satellites;

[0106] Step S8: Calculate the relative phase angle value of the constellation based on the constellation relative phase angle parameters; finally, give the constellation scheme of the active remote sensing satellite system.

[0107] In step S1, the payload detection capability includes the farthest effective range. According to the farthest effective distance Obtain the orbital height :

[0108]

[0109] in, The radius is the Earth's radius.

[0110] For example, the farthest effective distance The orbital altitude is 2600km. The calculated value is 510 km.

[0111] In step S2, the latitudinal range of the north-south detection area is the maximum value of the south and north latitudes of interest. Track inclination Calculated by the following formula:

[0112]

[0113] in The geocentric angle from the farthest point on the ground to the sub-satellite point is calculated by the following formula:

[0114]

[0115] in This is the maximum incident angle of the field of view that the payload can detect.

[0116] For example, if the latitudinal range of the north-south exploration area is from 10 degrees south latitude to 40 degrees north latitude, then... It is 40 degrees. The geocentric angle from the farthest point of the load on the ground to the sub-satellite point. The calculated angle is 22 degrees, representing the track inclination. The result calculated by the formula is 18 degrees.

[0117] In step S3, the payload detection capability includes the geocentric angle from the payload's farthest point on the ground to the nadir point. and the geocentric angle of the ground detectable range of the load , Calculated by the following formula:

[0118]

[0119] in It is the minimum incident angle of the field of view that the payload can detect.

[0120] Number of orbital surfaces This refers to the number of satellites in a north-south oriented group, calculated using the following formula:

[0121]

[0122] The function `ceil` returns the smallest integer greater than or equal to the specified expression. For example, it represents the geocentric angle from the farthest point on the ground to the nadir point. The geocentric angle of the ground detectable range is 22 degrees and the load is 22 degrees. The angle calculated by the formula is 18.7 degrees. Number of orbital planes. This is the number of satellites in a north-south direction group, which is calculated to be 6 using the formula.

[0123] In step S4, the tilt angle can be appropriately increased to 19° based on the actual overlap between the constellation and the payload's detection capabilities, thereby maximizing the detection latitude range.

[0124] In step S5, the orbital return period Calculated by the following formula:

[0125]

[0126] in, This is the Earth's gravitational constant. For example, the orbital return period. The calculation yields 94.8 minutes.

[0127] In step S6, the number of satellites in each orbital plane Calculated by the following formula:

[0128]

[0129] in To meet the revisit requirement of the probe.

[0130] Then the number of satellites Calculated by the following formula:

[0131]

[0132] For example, the revisit requirement of probes. If the interval is 60 minutes, then the number of satellites in each orbital plane The result calculated using the formula is 2. Therefore, the number of satellites is... The formula calculates to 12.

[0133] In step S7, the relative phase angle parameter of the constellation is the phase angle difference parameter F of the first satellite in the adjacent orbit, obtained from the table below, and the number of orbital planes is... The number of satellites in each orbital plane is .

[0134]

[0135] The relative phase angle parameter F of the constellation is 4, obtained from the table. Specifically, when P is 2, as N increases from 2, F increases accordingly from 0. With N constant, F cycles within the range of 0 to N-1 as P increases.

[0136] In step S8, the relative phase angle value of the constellation is the phase angle difference between the first satellite in the adjacent orbit. Calculated by the following formula:

[0137]

[0138] The final active remote sensing satellite system constellation scheme includes: orbital altitude, orbital inclination, number of orbital planes, number of satellites per orbital plane, and a description of the constellation's relative phase angle parameters.

[0139] For example, the relative phase angle of constellations The calculated value is 120 degrees. The final active remote sensing satellite system constellation scheme is as follows: orbital altitude 510km, orbital inclination 19 degrees, number of orbital planes 6, number of satellites per orbital plane 2, and constellation relative phase angle parameter 4.

[0140] This invention also provides a constellation formation system for north-south coordinated detection of an active remote sensing satellite system. Those skilled in the art can implement the constellation formation system for north-south coordinated detection of an active remote sensing satellite system by executing the steps of the constellation formation method for north-south coordinated detection of an active remote sensing satellite system. That is, the constellation formation method for north-south coordinated detection of an active remote sensing satellite system can be understood as a preferred embodiment of the constellation formation system for north-south coordinated detection of an active remote sensing satellite system.

[0141] Those skilled in the art will understand that, in addition to implementing the system, apparatus, and their modules provided by this invention in purely computer-readable program code, the same program can be implemented in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers by logically programming the method steps. Therefore, the system, apparatus, and their modules provided by this invention can be considered a hardware component, and the modules included therein for implementing various programs can also be considered structures within the hardware component; alternatively, modules for implementing various functions can be considered both software programs implementing the method and structures within the hardware component.

[0142] According to the present invention, a constellation formation system for north-south coordinated detection of an active remote sensing satellite system includes:

[0143] Module MA: Based on the payload detection capabilities of the active remote sensing satellite and the required latitudinal range for detection, select the orbital altitude and orbital inclination.

[0144] Module MB: Based on the orbital altitude and orbital inclination, a constellation scheme for the active remote sensing satellite system is obtained, which allows the north-south detectable range of multiple satellites to be stitched together.

[0145] The module MA includes:

[0146] Module M1: Determines the orbital altitude based on the payload detection capabilities of the active remote sensing satellite;

[0147] Module M2: Determines the orbital inclination angle based on the latitude range and orbital altitude of the north-south exploration area;

[0148] Module M3: Determines the number of satellite orbital planes based on the satellite payload's detection capabilities;

[0149] Module M4: Adjusts the orbital inclination based on the constellation and satellite payload detection capabilities to maximize the detection latitude range.

[0150] Preferably, in module M1, the load detection capability includes the furthest operating distance. According to the farthest effective distance Obtain the orbital height :

[0151]

[0152] in, The radius of the Earth;

[0153] In module M2, the latitude range of the north-south detection area is the maximum value of the south and north latitudes of interest. Track inclination Calculated by the following formula:

[0154]

[0155] in The geocentric angle from the farthest point on the ground to the sub-satellite point is calculated by the following formula:

[0156]

[0157] in The maximum angle of incidence in the field of view that the payload can detect;

[0158] In module M3, the payload detection capability includes the geocentric angle from the payload's farthest point on the ground to the nadir point. and the geocentric angle of the ground detectable range of the load , Calculated by the following formula:

[0159]

[0160] in The minimum incident angle of the field of view that the payload can detect;

[0161] Number of orbital surfaces This refers to the number of satellites in a north-south oriented group, calculated using the following formula:

[0162]

[0163] The function ceil returns the smallest integer that is greater than or equal to the specified expression;

[0164] In module M4, the orbital inclination is adjusted according to the actual overlap between the constellation and the payload's detection capabilities to maximize the detection latitude range.

[0165] Preferably, the module MB includes:

[0166] Module M5: Calculates the orbital return period based on the orbital height range and the orbital inclination angle;

[0167] Module M6: Based on the revisit requirements of the probe and the orbital return period, determine the number of satellites in each satellite orbital plane to obtain the total number of satellites;

[0168] Module M7: Selects the constellation relative phase angle parameters based on the number of satellites;

[0169] Module M8: Calculates the relative phase angle value of the constellation based on the constellation relative phase angle parameters; and finally provides a constellation scheme for the active remote sensing satellite system.

[0170] In module M5, the orbital return period Calculated by the following formula:

[0171]

[0172] in, The gravitational constant of Earth;

[0173] In module M6, the number of satellites per orbital plane Calculated by the following formula:

[0174]

[0175] in To meet the revisit requirement of the probe;

[0176] number of satellites Calculated by the following formula:

[0177]

[0178] In module M7, the constellation relative phase angle parameter is the constellation phase angle difference parameter F of the first satellite in the adjacent orbit;

[0179] In module M8, the relative phase angle value of the constellation is the phase angle difference between the first satellite in the adjacent orbit. The specific settings for the satellite orbit are calculated using the following formula:

[0180]

[0181] The constellation scheme of the active remote sensing satellite system is described by the parameters of orbital altitude, orbital inclination, number of orbital planes, number of satellites per orbital plane, and relative phase angle of the constellation.

[0182] In summary, the constellation formation method and system for north-south collaborative detection of active remote sensing satellite systems of the present invention fully utilizes the advantages of active remote sensing satellites, such as a large field of view and flexible detection range. The combined field of view of multiple active remote sensing satellite systems leverages the characteristics of the north-south combined motion of the constellation to achieve large-scale north-south collaborative detection. Addressing the needs of large satellite field of view, large detection area, north-south distribution of the detection area, and the requirement for quasi-simultaneous detection of the detection area, an improved constellation formation scheme is proposed. The algorithm of the present invention is reliable and stable, has a wide range of applications, and strong applicability, demonstrating good application and market prospects.

[0183] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, 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. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A constellation formation method for north-south coordinated detection in an active remote sensing satellite system, characterized in that, include: Step SA: Based on the payload detection capabilities of the active remote sensing satellite and the required latitudinal range for detection, select the orbital altitude and orbital inclination. Step SB: Based on the orbital altitude and orbital inclination, obtain the constellation scheme of the active remote sensing satellite system, so that the north-south detectable range of multiple satellites can be stitched together; The step SA includes: Step S1: Determine the orbital altitude based on the payload detection capabilities of the active remote sensing satellite; Step S2: Determine the orbital inclination angle based on the latitude range and orbital altitude of the north-south exploration area; Step S3: Determine the number of satellite orbital planes based on the satellite payload's detection capabilities; Step S4: Adjust the orbital inclination angle according to the constellation and satellite payload detection capabilities to maximize the detection latitude range; In step S1, the payload detection capability includes the farthest effective range. According to the farthest effective distance Obtain the orbital height : in, The radius of the Earth; In step S2, the latitudinal range of the north-south detection area is the maximum value of the south and north latitudes of interest. track inclination Calculated by the following formula: in The geocentric angle from the farthest point on the ground to the sub-satellite point is calculated by the following formula: in The maximum angle of incidence in the field of view that the payload can detect; In step S3, the payload detection capability includes the geocentric angle from the payload's farthest point on the ground to the nadir point. and the geocentric angle of the ground detectable range of the load , Calculated by the following formula: in The minimum angle of incidence for the payload to detect the field of view; Number of orbital surfaces This refers to the number of satellites in a north-south oriented group, calculated using the following formula: The function ceil returns the smallest integer that is greater than or equal to the specified expression; In step S4, the orbital inclination is adjusted according to the actual overlap between the constellation and the payload's detection capabilities to maximize the detection latitude range. The step SB includes: Step S5: Calculate the orbital return period based on the orbital height range and the orbital inclination angle; Step S6: Based on the revisit requirements of the probe and the orbital return period, determine the number of satellites in each satellite orbital plane to obtain the total number of satellites; Step S7: Select the constellation relative phase angle parameters according to the number of satellites; Step S8: Calculate the relative phase angle value of the constellation based on the constellation relative phase angle parameters; finally, provide the constellation scheme for the active remote sensing satellite system; In step S5, the orbital return period Calculated by the following formula: in, The gravitational constant of Earth; In step S6, the number of satellites in each orbital plane Calculated by the following formula: in To meet the revisit requirement of the probe; number of satellites Calculated by the following formula: In step S7, the constellation relative phase angle parameter is the constellation phase angle difference parameter F of the first satellite in the adjacent orbit; In step S8, the relative phase angle value of the constellation is the phase angle difference between the first satellite in the adjacent orbit. The specific settings for the satellite orbit are calculated using the following formula: The constellation scheme of the active remote sensing satellite system is described by the parameters of orbital altitude, orbital inclination, number of orbital planes, number of satellites per orbital plane, and relative phase angle of the constellation.

2. A constellation formation system for north-south coordinated detection by an active remote sensing satellite system, characterized in that, include: Module MA: Based on the payload detection capabilities of the active remote sensing satellite and the required latitudinal range for detection, select the orbital altitude and orbital inclination. Module MB: Based on the orbital altitude and orbital inclination, a constellation scheme for the active remote sensing satellite system is obtained, which allows the north-south detectable range of multiple satellites to be stitched together; The module MA includes: Module M1: Determines the orbital altitude based on the payload detection capabilities of the active remote sensing satellite; Module M2: Determines the orbital inclination angle based on the latitude range and orbital altitude of the north-south exploration area; Module M3: Determines the number of satellite orbital planes based on the satellite payload's detection capabilities; Module M4: Adjusts the orbital inclination angle based on the constellation and satellite payload detection capabilities to maximize the detection latitude range; In module M1, the payload detection capability includes the furthest operating distance. According to the farthest effective distance Obtain the orbital height : in, The radius of the Earth; In module M2, the latitude range of the north-south detection area is the maximum value of the south and north latitudes of interest. track inclination Calculated by the following formula: in The geocentric angle from the farthest point on the ground to the sub-satellite point is calculated by the following formula: in The maximum angle of incidence in the field of view that the payload can detect; In module M3, the payload detection capability includes the geocentric angle from the payload's farthest point on the ground to the nadir point. and the geocentric angle of the ground detectable range of the load , Calculated by the following formula: in The minimum angle of incidence for the payload to detect the field of view; Number of orbital surfaces This refers to the number of satellites in a north-south oriented group, calculated using the following formula: The function ceil returns the smallest integer that is greater than or equal to the specified expression; In module M4, the orbital inclination is adjusted according to the actual overlap between the constellation and payload detection capabilities to maximize the detection latitude range. The module MB includes: Module M5: Calculates the orbital return period based on the orbital height range and the orbital inclination angle; Module M6: Based on the revisit requirements of the probe and the orbital return period, determine the number of satellites in each satellite orbital plane to obtain the total number of satellites; Module M7: Selects the constellation relative phase angle parameters based on the number of satellites; Module M8: Calculates the relative phase angle value of the constellation based on the constellation relative phase angle parameters; and finally provides a constellation scheme for the active remote sensing satellite system. In module M5, the orbital return period Calculated by the following formula: in, The gravitational constant of Earth; In module M6, the number of satellites per orbital plane Calculated by the following formula: in To meet the revisit requirement of the probe; number of satellites Calculated by the following formula: In module M7, the constellation relative phase angle parameter is the constellation phase angle difference parameter F of the first satellite in the adjacent orbit; In module M8, the relative phase angle value of the constellation is the phase angle difference between the first satellite in the adjacent orbit. The specific settings for the satellite orbit are calculated using the following formula: The constellation scheme of the active remote sensing satellite system is described by the parameters of orbital altitude, orbital inclination, number of orbital planes, number of satellites per orbital plane, and relative phase angle of the constellation.

Images