Constellation system and sensing method

Abstract

The invention provides a constellation system and a sensing method. The constellation system comprises a plurality of satellites, the plurality of satellites operate on a plurality of orbit planes, a plurality of sensing devices are respectively installed on the plurality of satellites, and the sensing ranges of the plurality of sensing devices cover the whole world due to the arrangement of phase intervals among the plurality of orbit planes and the sensing range of each sensing device. The sensing range of the plurality of sensing devices covers the globe, so that the situation trend of the globe at any time and any place can be mastered conveniently.

Description

Technical Field

[0001] The present application relates to the field of satellites, and in particular to a constellation system and a sensing method. Background Art

[0002] At present, satellites play an important role in environmental monitoring, meteorological monitoring, security and other fields. However, the current satellite perception system can only sense in a specific area below the satellite orbit because the equipment carried by the satellite usually has a maximum field of view. Although there are many satellites in operation at home and abroad, the number of satellites is small, and the satellite constellation scale effect has not yet been formed, resulting in a limited satellite sensing range, which makes the role that the satellite perception system can play relatively limited. Therefore, how to achieve global coverage of the satellite sensing range to grasp the situation and trends at any time and any place in the world is a problem that needs to be solved. Summary of the invention

[0003] The embodiments of the present application provide a constellation system and a sensing method to enable the sensing range of the constellation system to cover the entire world.

[0004] In a first aspect, a constellation system is provided, comprising a plurality of satellites, wherein the plurality of satellites operate in a plurality of orbital planes, a plurality of sensor devices are respectively installed on the plurality of satellites, and the phase intervals between the plurality of orbital planes and the arrangement of the sensing range of each sensor device are arranged so that the sensing range of the plurality of sensor devices covers the entire globe.

[0005] In a possible implementation, each of the multiple sensing devices includes an electromagnetic spectrum detection device and / or a remote sensing imaging device.

[0006] In a possible implementation, each remote sensing imaging device includes an imaging system and an adjustment mechanism that are connected to each other, and the adjustment mechanism is used to adjust the imaging range of the imaging system.

[0007] In a possible implementation, a data processing system is installed on each of the multiple satellites, and the data processing system is used to process the sensing data collected by the sensor equipment on each satellite.

[0008] In one possible implementation, multiple communication devices are respectively installed on the multiple satellites, and each of the multiple communication devices includes a first communication unit and a second communication unit. The first communication unit is used for communication between satellites in the same orbit, and the second communication unit is used for communication between satellites in different orbits.

[0009] In a possible implementation, the multiple communication devices are laser communication devices.

[0010] In a possible implementation, the altitude of the orbits of the multiple satellites is lower than 500 km.

[0011] In a second aspect, a sensing method is provided, which is applied to a constellation system, wherein the constellation system includes multiple satellites, the multiple satellites operate in multiple orbital planes, and multiple sensing devices are respectively installed on the multiple satellites. The phase intervals between the multiple orbital planes and the arrangement of the sensing range of each sensing device make the sensing range of the multiple sensing devices cover the entire globe. Each of the multiple sensing devices includes an electromagnetic spectrum detection device and / or a remote sensing imaging device. The method includes: using the electromagnetic spectrum detection device to perform detection to determine whether there is a spectrum abnormality area; in response to detecting the spectrum abnormality area, using the remote sensing imaging device to image the spectrum abnormality area to obtain image data of the abnormal target; and sending the image data containing the abnormal target to a ground station.

[0012] In one possible implementation, in response to detecting a spectrum abnormality area, the spectrum abnormality area is imaged using the remote sensing imaging device to obtain image data of the abnormal target, including: determining a target imaging angle of the remote sensing imaging device according to a position of the spectrum abnormality area; and adjusting an imaging angle of an imaging system on the remote sensing imaging device to the target imaging angle to obtain image data of the abnormal target.

[0013] In a possible implementation, a data processing system is installed on each of the multiple satellites, and determining whether there is a spectrum abnormality area includes: using the data processing system to process the data collected by the electromagnetic spectrum detection equipment to determine whether there is a spectrum abnormality area; obtaining image data of the abnormal target includes: using the data processing system to process the image data collected by the remote sensing imaging equipment to obtain image data of the abnormal target.

[0014] In a possible implementation, sending the image data containing the abnormal target to the ground station includes: selecting a transmission link for the image data of the abnormal target from the inter-satellite links between the multiple satellites so that the transmission distance of the image data of the abnormal target is the shortest; and transmitting the image data of the abnormal target to the ground station using the transmission link.

[0015] The present application arranges the phase intervals between multiple orbital planes and the sensing range of each sensor so that the sensing range of multiple sensor devices installed on multiple satellites of the constellation system can cover the entire world, making it easier to grasp the situation and trends at any time and any place in the world. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the related technologies, the drawings required for use in the embodiments or the related technical descriptions will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application, and a person skilled in the art can also obtain other drawings based on these drawings.

[0017] Figure 1 This is an example diagram of a constellation system provided in an embodiment of the present application.

[0018] Figure 2 It is a schematic diagram of the structure of the constellation system satellite system provided in an embodiment of the present application.

[0019] Figure 3 It is a flow chart of a sensing method provided in an embodiment of the present application.

[0020] Figure 4 This is an example diagram of the constellation system workflow provided in an embodiment of the present application. DETAILED DESCRIPTION

[0021] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field belong to the scope of protection of this application.

[0022] At present, satellites play an important role in environmental monitoring, meteorological monitoring, security and other fields. However, the current satellite sensing system can only sense in a specific area below the satellite orbit, and cannot grasp the situation and trends at any time and any place in the world. Although there are many satellites in operation at home and abroad, the number of satellites is small, and the satellite constellation scale effect has not yet been formed, resulting in a limited satellite sensing range, which makes the role that the satellite sensing system can play relatively limited. Therefore, how to achieve global coverage of the satellite sensing range to grasp the situation and trends at any time and any place in the world is a problem that needs to be solved.

[0023] In view of the above problems, the present application proposes a constellation system. In the constellation system, multiple satellites are distributed on different orbital planes, and multiple satellites are respectively equipped with multiple sensing devices. By arranging the phase intervals between the multiple orbital planes and the sensing range of each sensor, the sensing range of multiple sensing devices installed on the multiple satellites of the constellation system can cover the entire world, making it easier to grasp the situation and trends at any time and any place in the world. The constellation system is described in detail below.

[0024] A constellation system is a satellite network consisting of multiple artificial satellites. Multiple satellites work together as a whole system. Multiple satellites can operate on multiple orbital planes. The orbital plane refers to the plane in which the satellite orbits the earth. This plane passes through the center of the earth. There are also multiple satellites on each orbital plane. Figure 1 An example of a constellation system is given. Multiple satellites are equipped with multiple sensor devices, that is, each of the multiple satellites is equipped with a sensor device. A sensor device refers to a device that can sense the information being measured and can transform the sensed information into the required form of information output according to a certain rule. There can be many types of sensor devices, for example, electromagnetic spectrum detection equipment, remote sensing imaging equipment, etc. The following takes electromagnetic spectrum detection equipment and remote sensing imaging equipment as examples to introduce sensor devices in more detail.

[0025] Electromagnetic spectrum detection equipment refers to equipment used to detect, measure and analyze various signals in the electromagnetic spectrum. The electromagnetic spectrum is an indispensable strategic resource in modern society, and is directly related to many aspects such as social economy and national security. In particular, it plays an important role in the maintenance of special frequency order in transportation such as aviation, Shunyun, and high-speed rail, as well as in the fields of security such as key protection and activity security. Electromagnetic spectrum detection equipment can detect the existence, intensity, frequency and other characteristics of electromagnetic waves, and can classify and identify these signals. Electromagnetic spectrum detection equipment can detect abnormal targets on the earth by detecting electromagnetic waves. The sensing range of electromagnetic spectrum detection equipment can be designed as needed. In order to achieve global coverage of the sensing range, the sensing range of the electromagnetic spectrum detection equipment can be designed to be a relatively large range. For example, the sensing range of the electromagnetic spectrum detection equipment can be ±65°. Although it is important for the sensing range of the constellation system to cover the world with a larger imaging range for the electromagnetic spectrum detection equipment. The larger the detection range of the electromagnetic spectrum detection equipment, the fewer satellites are required, and more costs can be saved. However, the role of the constellation system is not only to cover the world, but also to consider the accuracy of detection. It is meaningful to expand the detection range only when the detection accuracy can be guaranteed. Continuing with the example of the electromagnetic spectrum detection device with a sensing range of ±65°, within such a sensing range, the positioning accuracy of the electromagnetic spectrum detection device is 5km, and the circular error probable (CEP) is 90. CEP is an indicator used to measure the accuracy of the positioning system. In other words, when the sensing range of the electromagnetic spectrum detection device is ±65°, 90% of the detection results will fall within a circle with a radius of 5km centered on the true position. This design makes the electromagnetic spectrum detection device not only have a large sensing range, but also high positioning accuracy, which makes it possible for the sensing range of the constellation system to cover the world.

[0026] Remote sensing imaging equipment is a device that obtains images of the earth's surface from satellites. It detects and identifies various ground objects or phenomena by capturing electromagnetic wave information and scanning, photographing, transmitting and sorting this information.

[0027] The remote sensing imaging device includes an imaging system. Since the sensing range of the remote sensing imaging device is limited, in order to expand the sensing range of the remote sensing imaging device, the remote sensing imaging device may also include an adjustment mechanism. The adjustment mechanism may be used to adjust the imaging range of the imaging system. The adjustment mechanism may be, for example, a swing mirror, a focusing transmission assembly, etc. Taking the swing mirror as an example, the swing mirror is a mechanical device that can widen the field of view of the remote sensing imaging device and expand the imaging range by swinging scanning based on a reflector. The swing of the swing mirror may be set as required. In order to achieve global coverage of the sensing range, the swing range of the swing mirror may be designed to be a relatively large range. For example, the swing range of the swing mirror may be ±65°. When the swing range of the swing mirror is set to ±65°, the remote sensing imaging device may achieve ±65° side swing imaging of the subsatellite point. The subsatellite point refers to the point directly below the satellite in orbit. Although it is important for the remote sensing imaging device to obtain a larger imaging range for the sensing range of the constellation system to cover the world. The larger the imaging range of the remote sensing imaging device, the fewer satellites are required, and more costs can be saved. However, the role of the constellation system is not only to cover the world, but also to consider the resolution of the collected images. It is meaningful only when the resolution is sufficient to judge the relevant situation. The resolution of remote sensing imaging equipment is related to the orbital altitude. Taking the orbital altitude of the satellite in the constellation system as 300KM as an example, the resolution of the remote sensing imaging equipment in the constellation system at the subsatellite point can reach a ground resolution of 0.5m. When the remote sensing imaging equipment uses a swing mirror to achieve ±65° side swing imaging of the subsatellite point, the resolution range of the remote sensing imaging equipment in the constellation system is 0.5m (subsatellite point) to 3.2m (65° away from the subsatellite point). 3.2m (65° away from the subsatellite point) means that when the satellite deviates from the subsatellite point by 65°, the resolution of the remote sensing imaging equipment can reach a ground resolution of 3.2m. This is a relatively high resolution. This design enables the remote sensing imaging equipment to not only obtain a larger imaging range, but also a higher image resolution, which provides the possibility for the sensing range of the constellation system to cover the world.

[0028] Each sensing device may include one or more of an electromagnetic spectrum detection device and a remote sensing imaging device. In order to achieve global coverage of the sensing range of multiple sensing devices, the phase intervals between multiple track planes and the sensing range of each sensing device may be arranged.

[0029] Phase interval refers to the relative position relationship between satellites on different orbital planes, which can be described in degrees. There are many ways to arrange multiple orbits in a constellation system, such as non-equal interval distribution or equal interval distribution. In order to ensure the uniformity of satellite coverage areas in the constellation system, the satellites in the constellation system can be evenly spaced. If an evenly spaced distribution is adopted, the arrangement of phase intervals of multiple orbital planes must meet the following conditions: M = 180° / N, M is the phase interval between adjacent orbital planes, and N is the number of orbital planes in the constellation system. For example, if the constellation system has 20 orbital planes, the phase interval of the orbital plane is 9°. There is also a phase interval between each satellite on an orbital plane. The arrangement of satellites on an orbital plane can also be evenly spaced or unevenly spaced. If an evenly spaced distribution is adopted, the phase interval arrangement between adjacent satellites on an orbital plane must meet the following conditions: A = 360° / B, A is the phase interval between adjacent satellites on an orbital plane, and B is the number of satellites on each orbital plane in the constellation system. For example, if there are 40 satellites on each orbital plane, the phase interval between adjacent satellites on an orbital plane is 9°.

[0030] By arranging the phase intervals between multiple orbital planes and the sensing range of each sensing device, it is possible to achieve global coverage of the sensing range of multiple sensing devices. The following is an example that can make the sensing range of multiple sensing devices in a constellation system cover the world. For example, the constellation system consists of 800 satellites, 20 orbital planes, and 40 satellites in each orbital plane. The phase interval of the orbital plane is 9°, and the phase interval of each satellite in each orbital plane is 9°. Each satellite sensing device includes electromagnetic spectrum detection equipment and remote sensing imaging system equipment. The detection range of the electromagnetic spectrum detection equipment is designed to be ±65°, and the maneuvering range of the remote sensing imaging system equipment is designed to be ±65°. Through this design, it is possible to achieve global coverage of the sensing range of multiple sensing devices, making it easier to grasp the situation and trends at any time and any place in the world.

[0031] The above article introduces in detail the constellation system whose sensing range can cover the whole world. After the constellation system completes the detection of the whole world, it is usually necessary to transmit the detected data to the receiving station for processing through relay satellites or ground stations. However, since the constellation system contains data collected by multiple satellites, this will generate a large amount of data. Transmitting all the data to the receiving station for processing through satellites will cause data delay. This data delay may be hours or days, making it impossible to process the data in time. At the same time, if all the data collected by the constellation system are transmitted to the receiving station, there will be a lot of redundancy in the transmitted data. In order to shorten the data processing time, a data processing system can be installed on each of the multiple satellites. The data processing system is used to process the data collected by the sensor equipment on each satellite. For example, the data processing system can process the data obtained by the electromagnetic spectrum detector, extract abnormal target information, and give the abnormal target location. The data processing system can also process the image data obtained by the remote sensing imaging device, extract target slices, and perform data compression. The data processing system on the satellite can extract and process information of important areas or targets in orbit, directly obtain effective information, avoid the transmission of invalid redundant data, reduce ground processing delay time and data processing pressure, and improve the real-time performance of data processing.

[0032] In order to shorten the data processing time, multiple communication devices can be installed on multiple satellites in the constellation system. The communication device can include multiple communication units. The communication unit can be used for communication between satellites in the same orbit. For the convenience of description, the communication unit used for communication between satellites in the same orbit will be referred to as the first communication unit below. The communication unit can also be used for communication between satellites in different orbits. For the convenience of description, the communication unit used for communication between satellites in different orbits will be referred to as the second communication unit below. Through the first communication unit and the second communication unit, a data transmission network can be established between satellites within the entire constellation system, which expands the global data transmission capabilities and shortens the path for data transmission to domestic ground stations. Therefore, the real-time performance of data processing can be improved.

[0033] There are many types of communication equipment, such as laser communication equipment, microwave communication equipment, etc. Taking laser communication equipment as an example, laser communication equipment uses laser as carrier for data transmission. Laser communication equipment uses laser as carrier for transmission. It has a wide bandwidth and communication capacity, so its transmission rate is very fast, up to 1~10Gbps@1500KM. That is to say, at a distance of 1500KM, the rate of laser communication can reach 1~10G bits per second, which is a very high transmission rate. Therefore, multiple communication devices use laser communication equipment with high transmission rate to reduce data transmission delay and improve the real-time performance of data processing.

[0034] Optionally, in some embodiments, each satellite in the constellation system may be equipped with four laser communication devices, two of which are used to realize communication between satellites in the same orbit, and the other two are used to realize communication between satellites in different orbits. This configuration can improve the real-time performance of data processing.

[0035] Optionally, in some embodiments, the communication device may be a microwave communication device. Microwave communication devices use radio waves in the microwave frequency band for data transmission. Although the transmission rate is not as high as that of laser communication devices, microwave communication links have stronger penetration capabilities and more stable signals under severe weather conditions such as thick clouds or rain and snow. Therefore, the reliability of data transmission can be ensured under poor weather conditions.

[0036] As mentioned above, installing data processing systems and laser communication equipment on satellites can improve the real-time performance of data processing. Although the constellation system has shortened the time to process data, additional equipment may be required to achieve the corresponding functions. These devices will increase the weight or size of the satellite. Since satellites with an orbital altitude below 500km decay quickly, the orbital operating altitude of traditional satellites is generally above 500km, and the design indicators of satellite payloads are generally designed based on 500km and above. Under certain satellite weight, power consumption, size and other resource conditions, the satellite payload indicators generally reach the design capacity limit in a certain period of time. To further improve the indicators, the satellite resources paid may increase geometrically. Therefore, when the weight and size of the satellite increase, higher requirements will be placed on the carrying capacity of the launch vehicle, especially since the cost of satellite launch is still high, which is not conducive to the launch of multiple satellites with one rocket and the deployment of the constellation system. Within a certain orbital range, by reducing the orbital altitude, a linear increase in satellite payload capacity can generally be achieved. Therefore, in order to improve the payload capacity of the satellite and enable the constellation system to achieve more functions, the orbits of multiple satellites in the constellation system can be designed at any altitude below 500km. For example, the orbits of multiple satellites can be operated in a low orbit at an altitude of 300 km from the earth. At the same time, the satellites in the constellation system operate in a low orbit, which is closer to the ground, so the accuracy of satellite constellation sensing can be improved.

[0037] Although making multiple satellites in the constellation system operate at an orbit below 500KM can increase the satellite's payload capacity and achieve more functions, satellites below 500km orbital altitude decay quickly. Below 500KM altitude, the atmospheric density is relatively high, which causes more collisions between satellites and atmospheric molecules during operation, resulting in greater resistance. This resistance will slow down the satellite, gradually reduce its orbital altitude, and eventually cause the satellite to enter a denser atmosphere and burn up in friction. Therefore, in order to maintain multiple satellites in the satellite constellation at an altitude below 500KM and reduce the probability of attenuation, the satellite can be equipped with a Hall electric propulsion system. The Hall electric propulsion system has the characteristics of large specific impulse and light weight. Large specific impulse means that less propellant is required under the same speed increment requirement, which can save propellant and reduce the operating cost of the constellation system. In addition, the Hall electric propulsion system is light in weight, which can provide more space for increasing satellite payload.

[0038] Optionally, in some embodiments, orbit maintenance can be performed on each orbit or every multiple orbits in the constellation system according to the orbit attenuation situation. Performing orbit maintenance on each orbit or every multiple orbits according to the situation can save the operating cost of the constellation system compared to performing orbit maintenance on each orbit in any situation.

[0039] Optionally, in some embodiments, the reference orbit of each satellite is a circular orbit with an eccentricity of 0. An eccentricity of 0 means that the orbit is a perfect circle. In a circular orbit, the altitude and speed of the satellite are constant at any point in the orbit. This helps to keep the observation conditions of the satellite consistent, so that the constellation system can achieve uniform observation and coverage of the earth's surface.

[0040] Optionally, in some embodiments, the orbital inclination of each satellite is 87°. The orbital inclination is the angle between the orbital plane and the earth's plane. The inclination of 87° means that the satellite orbital plane is tilted more with respect to the equator, almost a polar orbit. Such an orbit allows the satellites in the constellation system to cover the polar regions of the earth, which helps to achieve global coverage of the sensing range.

[0041] The above article introduces the constellation system in detail. Figure 2 An exemplary introduction to the satellite composition of the constellation system is given.

[0042] The satellite may include a satellite platform 220 and a payload 210. The payload 210 may include, for example, a sensor device 211 and a data processing system 212. The sensor device 211 may include, for example, an electromagnetic spectrum detection device 213, a remote sensing imaging device 214, etc. The sensor device 211 and the data processing system 212 in the payload 210 have been described in detail above and will not be repeated here.

[0043] The satellite platform 220 may include a structural mechanism subsystem 221, a measurement and control data transmission subsystem 222, an energy subsystem 223, an integrated electronic subsystem 224, a laser communication subsystem 225, a thermal control subsystem 226, an attitude and orbit control subsystem 227, etc. The following is a detailed introduction to each part of the satellite platform 220.

[0044] (1) Structural mechanism subsystem 221: used to provide support and layout for satellite subsystems and single units.

[0045] (2) Measurement, control and data transmission subsystem 222: used for satellite downlink telemetry, uplink remote control commands, storage of electromagnetic spectrum payload data and optical payload data, and high-speed transmission to ground data receiving stations.

[0046] (3) Energy subsystem 223: Provides energy for the entire satellite and performs energy management. The satellite can be equipped with a two-dimensional sailboard drive mechanism to adjust the sailboard normal to point to the sun according to the lighting conditions of the satellite in orbit. This ensures that the satellite can still obtain sufficient energy when the three axes are stabilized to the ground.

[0047] (4) Integrated Electronic Subsystem 224: It is the core of satellite information data processing and is used to complete satellite flight management, onboard integrated data management, satellite attitude and orbit control management, satellite thermal control management, global navigation satellite system (GNSS) signal processing, onboard data processing, satellite remote control and telemetry, etc.

[0048] (5) Laser communication subsystem 225: The laser communication system uses data transmission via inter-satellite links on the same orbit and inter-satellite links on different orbits, and is an important component in connecting the data of each satellite in the constellation system. There are four laser communication devices on each satellite, corresponding to the two satellites in front and behind on the same orbit, and the two satellites in the left and right directions on different orbits. The laser communication rate is 1 to 10 Gbps @ 1500 km.

[0049] (6) Thermal Control Subsystem 226: Take necessary thermal control measures based on the satellite's orbit, attitude, configuration, instrument layout, thermal power consumption, operating mode, and environmental conditions to ensure that all equipment on board maintains operation at the specified temperature during the entire mission, thereby ensuring the smooth completion of various missions during the flight.

[0050] (7) Attitude and orbit control subsystem 227: It is used to ensure the satellite attitude pointing required during the satellite mission and to meet the three-axis stable attitude pointing requirements of the entire satellite to the ground when the satellite payload is working normally. When the satellite's orbital altitude is lower than 500 km, for example, when the satellite is operating in a 300 km ultra-low orbit, the orbital altitude decays rapidly, and a Hall electric propulsion orbit control system is used, with the thrust normal direction facing the -X direction. According to the actual orbital decay of the satellite in orbit, orbit maintenance is performed every orbit or every few orbits. At the same time, the phase maintenance of each satellite in the constellation system is also completed by the attitude and orbit control subsystem. Therefore, the attitude and orbit control subsystem is an important part of the constellation system.

[0051] The above article introduces the constellation system in detail. Figure 3 The sensing method of the constellation system in the embodiment of the present application is introduced in more detail by way of example. The sensing method can be applied to the constellation system described above. Specifically, the constellation system may include multiple satellites, the multiple satellites operate on multiple orbital planes, multiple sensing devices are respectively installed on the multiple satellites, the phase intervals between the multiple orbital planes and the arrangement of the sensing range of each sensing device make the sensing range of the multiple sensing devices cover the entire world, and each of the multiple sensing devices includes an electromagnetic spectrum detection device and / or a remote sensing imaging device.

[0052] Reference Figure 3 , Figure 3 The sensing method includes step S310, step S320 and step S330.

[0053] In step S310, electromagnetic spectrum detection equipment is used to perform detection to determine whether there is an abnormal spectrum area.

[0054] A spectrum anomaly area refers to an area where the electromagnetic environment is significantly different from the normal state or has undergone unexpected changes. Electromagnetic spectrum detection equipment can determine whether there is a spectrum anomaly area by detecting and collecting electromagnetic spectrum data, and determining the location, time, type, etc. of the target based on the information extracted from the collected electromagnetic spectrum data.

[0055] In step S320, in response to detecting the abnormal spectrum region, the abnormal spectrum region is imaged using a remote sensing imaging device to obtain image data of the abnormal target.

[0056] The method of using remote sensing imaging equipment to image the spectrum abnormal area to obtain image data of the abnormal target may include the following steps:

[0057] Step 1: Determine the target imaging angle of the remote sensing imaging device based on the location of the spectrum anomaly area.

[0058] The imaging angle of the remote sensing imaging equipment can be calculated according to the mission planning.

[0059] Step 2: Adjust the imaging angle of the imaging system on the remote sensing imaging device to the target imaging angle to obtain image data of the abnormal target.

[0060] The imaging angle adjustment of the imaging system on the remote sensing imaging device can be achieved by adjusting the angle of the swing mirror. With the help of the swing mirror, the remote sensing imaging device can perform high-resolution imaging of the target.

[0061] The above steps S310 and S320 can process the electromagnetic spectrum data collected by the electromagnetic spectrum equipment and the image data collected by the remote sensing imaging equipment with the help of the data processing system installed on each satellite. For example, the data collected by the electromagnetic spectrum equipment can be processed by the data processing system to extract effective information within 1 to 2 seconds to determine whether there is an abnormal spectrum area. For another example, the image data collected by the remote sensing imaging equipment can be processed by the data processing system to extract slice data of the target image data. The slice data may include image slices of abnormal targets, longitude, latitude, imaging angle, imaging time and other information of the target. By processing the collected image data by the data processing system on the satellite to obtain the image data of the abnormal target, redundant data can be eliminated, and effective information can be directly obtained, reducing the pressure of data transmission and ground processing.

[0062] In step S330, the image data containing the abnormal target is sent to the ground station.

[0063] Sending image data containing abnormal targets to a ground station may include the following steps:

[0064] Step 3: Select a transmission link for the image data of the abnormal target from the inter-satellite links between multiple satellites so that the transmission distance of the image data of the abnormal target is the shortest.

[0065] The shortest transmission distance of the image data of the anomaly target can be calculated by the constellation ephemeris. The constellation ephemeris is a data set that describes and predicts the position and motion of satellites in space. It can use orbital parameters to determine the position and velocity of the satellite at any given time based on Kepler's laws.

[0066] Step 4: Use the transmission link to transmit the image data of the abnormal target to the ground station.

[0067] There are many transmission links for transmitting abnormal target image data to the ground station, such as laser communication links, microwave communication links, etc. A suitable communication transmission link can be selected according to different weather conditions in the area above the ground station. For example, when the weather in the area above the ground station is clear and the atmospheric transparency is high, a laser communication link can be selected. The transmission rate of the laser communication link is high, so the real-time performance of data transmission can be improved. However, under severe weather conditions such as thick clouds or rain and snow, a microwave communication link can be selected. Since the microwave communication link has stronger penetration ability and more stable signals under severe weather conditions, the reliability of data transmission can be ensured.

[0068] Combine the following Figure 4 The workflow of the constellation system is described in more detail. In the example below, the adjustment mechanism interconnected with the imaging system adopts a swing mirror, the communication equipment adopts a laser communication equipment, and the satellite orbit altitude is selected to be 300KM. It should be noted that this example is only to help those skilled in the art understand the embodiments of the present application, and is not intended to limit the embodiments of the present application to the specific types or scenarios illustrated. Those skilled in the art can obviously make various equivalent modifications or changes based on the examples given below, and such modifications or changes also fall within the scope of the embodiments of the present application.

[0069] Each satellite in the constellation system is three-axis stable pointing to the earth, the detection range of the electromagnetic detection equipment is ±65°, and the central axis of the detection field of view points to the +Z direction of the satellite body. The 0.5m high-resolution remote sensing imaging equipment has a ±65° swing mirror, which can achieve ±65° side swing imaging of the sub-satellite point, that is, the imaging range is ±65°.

[0070] In step S410, the electromagnetic spectrum device performs electromagnetic spectrum detection.

[0071] For example, the electromagnetic payload is often powered on during in-orbit flight to perform electromagnetic spectrum detection and collect electromagnetic spectrum data, which are then sent to the storage module of the measurement, control and data transmission subsystem.

[0072] In step S420, the electromagnetic spectrum detection data is processed on-orbit.

[0073] For example, the collected electromagnetic spectrum data is sent from the storage module of the measurement and control data transmission subsystem to the data processing system. After being processed by the data processing system, effective information such as the location, time, type, etc. of the target is extracted within 1 to 2 seconds.

[0074] In step S430, based on the on-orbit processing of the detection data, it is determined whether an abnormal target is found.

[0075] For example, judging whether an abnormal target is found based on the electromagnetic spectrum data processed on orbit.

[0076] In step S440, it is determined that an abnormal target is found, and it is determined whether the data is transmitted back to the ground station or image confirmation is performed through remote sensing imaging equipment.

[0077] For example, if it is an abnormal target, the following judgment can be made:

[0078] (1) On the one hand, it is determined whether to transmit back to the ground station. If it is chosen to transmit back to the ground station, the laser communication equipment returns data to the process; if it is not chosen to transmit back to the ground station, the electromagnetic spectrum real-time detection process is returned;

[0079] (2) On the other hand, it is determined whether image confirmation is required through high-resolution remote sensing imaging. If image confirmation is not required, the process returns to the real-time electromagnetic spectrum detection process; if image confirmation is required, the imaging angle and imaging time are calculated through task planning, the swing mirror angle of the remote sensing imaging equipment is adjusted, and high-resolution imaging of abnormal targets is performed. The acquired image raw data is sent to the memory of the measurement and control digital transmission subsystem.

[0080] In step S450, the image data is processed on-track.

[0081] For example, the collected image data is sent from the memory of the measurement and control data transmission subsystem to the data processing system, and after the image data is processed on-orbit, the slice data of the abnormal target is extracted. The slice data includes the image slice of the target, the longitude, latitude, imaging angle, imaging time and other information of the target.

[0082] In step S460, it is determined whether image slice information is generated.

[0083] For example, if there is no image slicing information, the process returns to the real-time electromagnetic spectrum detection process and the electromagnetic spectrum detection continues; if there is an image slice, indicating that an abnormal target has been found and confirmed by the image slice, the laser communication equipment returns data process.

[0084] In step S470, the shortest transmission path is selected and data is transmitted to the ground station using the transmission link.

[0085] For example, after receiving the slice signal or electromagnetic information of an abnormal target, the satellite's laser communication subsystem automatically selects the shortest path through constellation ephemeris calculation and transmits it to the domestic ground station via the laser intersatellite link. If the image slice data or the target information after intelligent processing of the electromagnetic spectrum is transmitted to the country via the intersatellite link, the laser communication pair is selected to be transmitted underground or transmitted to the ground station via microwave according to the weather conditions in the airspace above the domestic ground station.

[0086] It should be understood that in the embodiment of the present application, "B corresponding to A" means that B is associated with A, and B can be determined according to A. However, it should also be understood that determining B according to A does not mean determining B only according to A, and B can also be determined according to A and / or other information.

[0087] It should be understood that the term "and / or" in this article is only a description of the association relationship of the associated objects, indicating that there can be three relationships. For example, A and / or B can represent: A exists alone, A and B exist at the same time, and B exists alone. In addition, the character " / " in this article generally indicates that the associated objects before and after are in an "or" relationship.

[0088] It should be understood that in the various embodiments of the present application, the size of the serial numbers of the above-mentioned processes does not mean the order of execution. The execution order of each process should be determined by its function and internal logic, and should not constitute any limitation on the implementation process of the embodiments of the present application.

[0089] In the several embodiments provided in the present application, it should be understood that the disclosed systems, devices and methods can be implemented in other ways. For example, the device embodiments described above are only schematic. For example, the division of the units is only a logical function division. There may be other division methods in actual implementation, such as multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. Another point is that the mutual coupling or direct coupling or communication connection shown or discussed can be through some interfaces, indirect coupling or communication connection of devices or units, which can be electrical, mechanical or other forms.

[0090] The units described as separate components may or may not be physically separated, and the components shown as units may or may not be physical units, that is, they may be located in one place or distributed on multiple network units. Some or all of the units may be selected according to actual needs to achieve the purpose of the solution of this embodiment.

[0091] In addition, each functional unit in each embodiment of the present application may be integrated into one processing unit, or each unit may exist physically separately, or two or more units may be integrated into one unit.

[0092] In the above embodiments, it can be implemented in whole or in part by software, hardware, firmware or any combination thereof. When implemented using software, it can be implemented in whole or in part in the form of a computer program product. The computer program product includes one or more computer instructions. When the computer program instructions are loaded and executed on a computer, the process or function described in the embodiment of the present application is generated in whole or in part. The computer may be a general-purpose computer, a special-purpose computer, a computer network, or other programmable device. The computer instructions may be stored in a computer-readable storage medium, or transmitted from one computer-readable storage medium to another computer-readable storage medium, for example, the computer instructions may be transmitted from a website site, computer, server or data center by wired (e.g., coaxial cable, optical fiber, digital subscriber line (digital subscriber line, DSL)) or wireless (e.g., infrared, wireless, microwave, etc.) mode to another website site, computer, server or data center. The computer-readable storage medium may be any available medium that can be read by a computer or a data storage device such as a server or data center that includes one or more available media integrated. The available medium may be a magnetic medium (eg, a floppy disk, a hard disk, a magnetic tape), an optical medium (eg, a digital video disc (DVD)), or a semiconductor medium (eg, a solid state disk (SSD)).

[0093] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any person skilled in the art who is familiar with the present technical field can easily think of changes or substitutions within the technical scope disclosed in the present application, which should be included in the protection scope of the present application. Therefore, the protection scope of the present application should be based on the protection scope of the claims.

Claims

1. A constellation system, characterized in that: The constellation system includes multiple satellites, which operate in multiple orbital planes. Multiple sensor devices are respectively installed on the multiple satellites. The phase intervals between the multiple orbital planes and the arrangement of the sensing range of each sensor device enable the sensing range of the multiple sensor devices to cover the entire world.

2. The constellation system according to claim 1, characterized in that: Each of the plurality of sensing devices comprises an electromagnetic spectrum detection device and / or a remote sensing imaging device.

3. The constellation system according to claim 2, characterized in that: Each remote sensing imaging device comprises an imaging system and an adjusting mechanism which are connected to each other. The adjusting mechanism is used to adjust the imaging range of the imaging system.

4. The constellation system according to claim 1, characterized in that: A data processing system is installed on each of the multiple satellites, and the data processing system is used to process the sensing data collected by the sensor equipment on each satellite.

5. The constellation system according to claim 1, characterized in that: A plurality of communication devices are respectively installed on the plurality of satellites, and each of the plurality of communication devices includes a first communication unit and a second communication unit. The first communication unit is used for communication between satellites in the same orbit, and the second communication unit is used for communication between satellites in different orbits.

6. The constellation system according to claim 5, characterized in that: The plurality of communication devices are laser communication devices.

7. The constellation system according to any one of claims 1 to 6, characterized in that: The orbits of the plurality of satellites have an altitude below 500 km.

8. A sensing method, characterized in that: The method is applied to a constellation system, wherein the constellation system includes a plurality of satellites, the plurality of satellites are operated on a plurality of orbital planes, a plurality of sensing devices are respectively installed on the plurality of satellites, the phase intervals between the plurality of orbital planes and the arrangement of the sensing range of each sensing device enable the sensing range of the plurality of sensing devices to cover the entire globe, and each of the plurality of sensing devices includes an electromagnetic spectrum detection device and / or a remote sensing imaging device, The method comprises: Using the electromagnetic spectrum detection equipment to detect whether there is an abnormal spectrum area; In response to detecting the abnormal spectrum area, imaging the abnormal spectrum area using the remote sensing imaging device to obtain image data of the abnormal target; The image data containing the abnormal target is sent to a ground station.

9. The method according to claim 8, characterized in that In response to detecting the abnormal spectrum area, imaging the abnormal spectrum area using the remote sensing imaging device to obtain image data of the abnormal target includes: Determining a target imaging angle of the remote sensing imaging device according to the position of the spectrum abnormal area; The imaging angle of the imaging system on the remote sensing imaging device is adjusted to the target imaging angle to obtain image data of the abnormal target.

10. The method according to claim 8 or 9, characterized in that: Each of the plurality of satellites is equipped with a data processing system, and the determining whether there is a spectrum abnormality area includes: Using the data processing system to process the data collected by the electromagnetic spectrum detection device to determine whether there is an abnormal spectrum area; The step of acquiring image data of an abnormal target includes: The data processing system is used to process the image data collected by the remote sensing imaging device to obtain the image data of the abnormal target.

11. The method according to claim 8, characterized in that The sending of the image data containing the abnormal target to the ground station comprises: Selecting a transmission link for the image data of the abnormal target from the inter-satellite links between the plurality of satellites so that the transmission distance of the image data of the abnormal target is the shortest; The image data of the abnormal target is transmitted to the ground station using the transmission link.

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