WO2021004233A1 - 卫星通信方法、装置、终端设备、卫星及可读存储介质 - Google Patents
卫星通信方法、装置、终端设备、卫星及可读存储介质 Download PDFInfo
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- WO2021004233A1 WO2021004233A1 PCT/CN2020/096151 CN2020096151W WO2021004233A1 WO 2021004233 A1 WO2021004233 A1 WO 2021004233A1 CN 2020096151 W CN2020096151 W CN 2020096151W WO 2021004233 A1 WO2021004233 A1 WO 2021004233A1
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- system message
- terminal device
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
- H04B7/185—Space-based or airborne stations; Stations for satellite systems
- H04B7/18523—Satellite systems for providing broadcast service to terrestrial stations, i.e. broadcast satellite service
- H04B7/18526—Arrangements for data linking, networking or transporting, or for controlling an end to end session
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
- H04B7/185—Space-based or airborne stations; Stations for satellite systems
- H04B7/1851—Systems using a satellite or space-based relay
- H04B7/18519—Operations control, administration or maintenance
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/13—Receivers
- G01S19/24—Acquisition or tracking or demodulation of signals transmitted by the system
- G01S19/27—Acquisition or tracking or demodulation of signals transmitted by the system creating, predicting or correcting ephemeris or almanac data within the receiver
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
- H04B7/185—Space-based or airborne stations; Stations for satellite systems
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
- H04B7/185—Space-based or airborne stations; Stations for satellite systems
- H04B7/1853—Satellite systems for providing telephony service to a mobile station, i.e. mobile satellite service
- H04B7/18532—Arrangements for managing transmission, i.e. for transporting data or a signalling message
- H04B7/18534—Arrangements for managing transmission, i.e. for transporting data or a signalling message for enhancing link reliablility, e.g. satellites diversity
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
- H04B7/185—Space-based or airborne stations; Stations for satellite systems
- H04B7/18578—Satellite systems for providing broadband data service to individual earth stations
- H04B7/18582—Arrangements for data linking, i.e. for data framing, for error recovery, for multiple access
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
- H04B7/185—Space-based or airborne stations; Stations for satellite systems
- H04B7/18578—Satellite systems for providing broadband data service to individual earth stations
- H04B7/18586—Arrangements for data transporting, e.g. for an end to end data transport or check
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04W—WIRELESS COMMUNICATION NETWORKS
- H04W40/00—Communication routing or communication path finding
- H04W40/24—Connectivity information management, e.g. connectivity discovery or connectivity update
- H04W40/246—Connectivity information discovery
Definitions
- the embodiments of the present application relate to communication technology, and in particular to a satellite communication method, device, terminal device, satellite, and readable storage medium.
- Satellite communication is communication between two or more terminal devices that uses artificial earth satellites as relay stations to relay radio waves. Compared with terrestrial communication, satellite communication has the advantages of wide coverage, large communication capacity, good transmission quality, convenient and rapid networking, and easy realization of seamless global links. The use of satellite communication enables users to conduct voice calls, video calls, and video viewing services in any area of the world. In satellite communication, how to realize the information interaction between the satellite and the terminal equipment so that the terminal equipment can obtain the ephemeris data of the satellite in time is an important research topic.
- the information interaction method between the satellite and the terminal device involved in the traditional technology is mainly the interaction method between the satellite and the terminal device in the global positioning system (GPS).
- GPS global positioning system
- the satellite sends the ephemeris data of the satellite to the terminal device through the navigation message.
- the terminal equipment selects the appropriate satellite and captures the selected satellite based on the ephemeris data obtained from the navigation message.
- the length of each frame of navigation message is 30 seconds/1500 bits.
- the terminal device needs to continuously monitor the navigation message for more than 750 seconds.
- the embodiments of the present application provide a satellite communication method, device, terminal equipment, satellite, and readable storage medium, which can meet the requirements of low overhead and low delay in satellite communication.
- an embodiment of the present application provides a satellite communication method.
- a terminal device receives a first system message sent by a first satellite.
- the first system message is used to indicate that the first satellite is at the ephemeris reference moment. Flat anomaly.
- the terminal device can determine the topology of the satellite network to which the first satellite belongs according to the first system message.
- the terminal device receives the first system message sent by the satellite according to the preset period, and the system message is used to indicate the mean anomaly of the currently observed satellite at the reference moment, based on the first system message and the terminal device pre-stored With the ephemeris parameters that will not change, the terminal device can determine the currently observed satellites and the position information of other satellites in the satellite network, and then can obtain the satellite network topology. Since the first system message is only used to indicate the mean anomaly angle of the currently observed satellite at the reference moment, that is, the first system message only needs to carry fewer parameters. Therefore, the terminal device only needs less time delay and smaller The overhead of the satellite network can be determined, so that the satellite communication system can meet the requirements of low delay and low overhead.
- the first system message may include the first satellite identifier, the ephemeris reference moment, and the mean anomaly of the first satellite at the ephemeris reference moment. Through these parameters, the mean anomaly angle of the first satellite at the ephemeris reference moment can be obtained.
- the first system message may also include an identifier of a satellite that is currently online and/or an identifier of a satellite that is currently offline.
- the terminal equipment can be updated according to the identification of the latest online satellite and/or the latest offline satellite carried by it.
- the locally stored satellite list makes the operating status of the satellites in the locally stored satellite list consistent with the actual operating status, thereby ensuring that the terminal device can communicate with the satellite normally.
- the terminal device may send a first request message to the first satellite, where the first request message is used to request the first satellite to send the first system message.
- the first satellite sends the first system message to the terminal device according to the first request message.
- the terminal device actively requests the first system message from the first satellite.
- the first satellite may also actively send the foregoing first request message according to a preset period.
- the terminal device may control the sending of the first request message through a timer.
- the initial value of the timer can be indicated by the network device to the terminal device when the terminal device is successfully registered in the network.
- the timer resets the initial value and starts timing.
- the terminal device is triggered to send the aforementioned first request message to the satellite to request the satellite to send the first system message, and at the same time, the terminal device terminates the timer.
- the terminal device logs off from the network, the timer expires.
- the terminal device may send a second request message to the second satellite, and the second request message is used to request to obtain the second satellite Further, the terminal device receives a second system message sent by the second satellite, and the second system message is used to indicate the ephemeris parameter of the second satellite.
- the second satellite and the first satellite may be the same satellite or different satellites.
- the terminal device may send the second request message to the second satellite when it first accesses the network, and receive the second system message sent by the second satellite.
- the above-mentioned second system message includes the square root of the semi-major axis of the orbit of the satellite network, the eccentricity, the angular distance of perigee, the inclination of the orbit at the reference time, and the right ascension of the ascending node.
- An optional above-mentioned second system message further includes the identifier of the second satellite, the ephemeris reference moment, and the mean anomaly of the second satellite at the ephemeris reference moment.
- the embodiments of the present application provide a satellite communication method.
- a first satellite sends a first system message to a terminal device so that the terminal device can determine the satellite network to which the first satellite belongs according to the first system message.
- Topology wherein the first system message is used to indicate the mean anomaly of the first satellite at the ephemeris reference moment.
- the first system message includes the identity of the first satellite, the ephemeris reference time, and the mean anomaly of the first satellite at the ephemeris reference time.
- the above-mentioned first system message further includes an identifier of a satellite currently online and/or an identifier of a satellite currently offline.
- the first satellite may also receive a first request message sent by the terminal device, where the first request message is used to request the first satellite to send the The first system message. After receiving the first request message, the first satellite sends the first system message to the terminal device according to the first request message.
- the first satellite sends the first system message according to the request of the terminal device.
- the first satellite may also actively send the foregoing first request message according to a preset period.
- the first satellite may also receive a second request message sent by the above-mentioned terminal device, the second request message is used to request to obtain the ephemeris parameters of the second satellite, and according to the above-mentioned second request message , Sending a second system message to the terminal device, where the second system message is used to indicate the ephemeris parameter of the second satellite.
- the second satellite and the first satellite are the same satellite.
- the second system message includes the square root of the semi-major axis of the orbit of the satellite network, the eccentricity, the angular distance of perigee, the inclination of the orbit at the reference time, and the right ascension of the ascending node.
- the second system message further includes the identifier of the second satellite, the ephemeris reference time, and the mean anomaly of the second satellite at the ephemeris reference time.
- an embodiment of the present application provides a satellite communication device, which includes:
- the receiving module is used to receive the first system message sent by the first satellite, and the first system message is used to indicate the mean anomaly of the first satellite at the ephemeris reference moment; the processing module is used to A system message to determine the topology of the satellite network to which the first satellite belongs.
- the first system message includes the identity of the first satellite, the ephemeris reference moment, and the mean anomaly of the first satellite at the ephemeris reference moment.
- the first system message also includes an identifier of a satellite currently online and/or an identifier of a satellite currently offline.
- the device further includes:
- the sending module is configured to send a first request message to the first satellite, and the first request message is used to request the first satellite to send the first system message.
- the device further includes:
- the sending module is used to send a second request message to the second satellite, the second request message is used to request to obtain the ephemeris parameters of the second satellite; the receiving module is also used to receive the second satellite sent by the second satellite Two system messages, the second system messages are used to indicate the ephemeris parameters of the second satellite.
- the second system message includes the square root of the semi-major axis of the orbit of the satellite network, the eccentricity, the angular distance of perigee, the inclination of the orbit at the reference time, and the right ascension of the ascending node.
- the second system message further includes the identifier of the second satellite, the ephemeris reference time, and the mean anomaly of the second satellite at the ephemeris reference time.
- an embodiment of the present application provides a satellite communication device, which includes:
- the processing module is configured to send a first system message to a terminal device through the sending module, so that the terminal device determines the topology of the satellite network to which the first satellite belongs according to the first system message.
- a system message is used to indicate the mean anomaly angle of the first satellite at the ephemeris reference moment.
- the first system message includes the identity of the first satellite, the ephemeris reference moment, and the mean anomaly of the first satellite at the ephemeris reference moment.
- the first system message also includes an identifier of a satellite currently online and/or an identifier of a satellite currently offline.
- the device further includes:
- a receiving module configured to receive a first request message sent by the terminal device, the first request message being used to request the first satellite to send the first system message;
- the sending module is specifically configured to send the first system message to the terminal device according to the first request message.
- the device further includes:
- a receiving module configured to receive a second request message sent by the terminal device, where the second request message is used to request to obtain ephemeris parameters of the second satellite;
- the sending module is further configured to send a second system message to the terminal device according to the second request message, where the second system message is used to indicate the ephemeris parameter of the second satellite.
- the second system message includes the square root of the semi-major axis of the orbit of the satellite network, the eccentricity, the angular distance of perigee, the inclination of the orbit at the reference time, and the right ascension of the ascending node.
- the second system message further includes the identifier of the second satellite, the ephemeris reference time, and the mean anomaly of the second satellite at the ephemeris reference time.
- an embodiment of the present application provides a terminal device.
- the terminal device includes a memory, a processor, and a transceiver; the processor is configured to couple with the memory, read and execute instructions in the memory, In order to implement the method steps described in the first aspect; the transceiver is coupled with the processor, and the processor controls the transceiver to send and receive messages.
- an embodiment of the present application provides a satellite including: a memory, a processor, and a transceiver; the processor is configured to couple with the memory, read and execute instructions in the memory, so as to implement the second The method steps described in the aspect; the transceiver is coupled with the processor, and the processor controls the transceiver to send and receive messages.
- an embodiment of the present application provides a computer program product, the computer program product includes computer program code, when the computer program code is executed by a computer, the computer executes the first aspect or the second aspect. The method described.
- an embodiment of the present application provides a computer-readable storage medium that stores computer instructions.
- the computer instructions When the computer instructions are executed by a computer, the computer executes the first aspect or the second aspect. Instructions for the method described in the aspect.
- an embodiment of the present application provides a chip, which is connected to a memory, and is used to read and execute a software program stored in the memory to implement the method provided in the first aspect or the second aspect. .
- an embodiment of the present application provides a device including: an input interface circuit, a logic circuit, and an output interface circuit, wherein the logic circuit is used to execute the method described in the first aspect above, or the second aspect above The method described.
- Figure 1 is a schematic diagram of the structure of a navigation message
- Figure 2 is a schematic diagram of GPS application scenarios
- FIG. 3 is a schematic diagram of an exemplary system architecture of a communication method provided by an embodiment of the application.
- Figure 4 is a schematic diagram of satellite orbit parameters
- Figure 5 is a schematic diagram of satellite orbit parameters
- FIG. 6 is an interaction flowchart of Embodiment 1 of the communication method provided by an embodiment of this application.
- FIG. 7 is an interaction flowchart of Embodiment 2 of the communication method provided by an embodiment of this application.
- FIG. 8 is an interaction flowchart of Embodiment 3 of the communication method provided by an embodiment of this application.
- FIG. 9 is a module structure diagram of a satellite communication device provided by an embodiment of the application.
- FIG. 10 is a block diagram of another satellite communication device provided by an embodiment of the application.
- FIG. 11 is a module structure diagram of another satellite communication device provided by an embodiment of the application.
- FIG. 12 is a schematic structural diagram of a terminal device provided by an embodiment of this application.
- FIG. 13 is a schematic structural diagram of a satellite provided by an embodiment of this application.
- the navigation message includes data codes for navigation information such as satellite ephemeris, satellite working status, time system, satellite clock running status, orbital perturbation parameters, atmospheric refraction changes, and C/A code capture codes.
- the navigation message is composed of main frame, sub-frame, word code and page.
- Figure 1 is a schematic diagram of the structure of a navigation message. As shown in Figure 1, the basic unit of the navigation message is a 1500-bit main frame. A main frame includes 5 subframes. Each subframe of the first subframe, the second subframe, and the third subframe includes 10 characters, each character includes 30 bits, and the transmission time of each bit is 0.02 seconds.
- the 3 subframes are used to broadcast the satellite's ephemeris and clock correction parameters.
- the 4th subframe and the 5th subframe respectively include 25 pages, each page includes 750 bits, and the transmission time of each bit is 0.02 seconds.
- the 2 subframes are used to broadcast the almanac of all 25 satellites.
- the transmission rate of the navigation message is 50 bits per second, and one main frame is 1500 bits. Therefore, the transmission time of one main frame of the navigation message is 30 seconds.
- the ratio of 1500 of 1 main frame is allocated to 5 subframes, each with 300 bits. Therefore, the first subframe, the second subframe, and the third subframe can be repeated every 30 seconds and updated every hour.
- One main frame can transmit one page each in the 4th subframe and the 5th subframe.
- the 4th subframe and the 5th subframe require 25 main frames to transmit. Therefore, a complete navigation message requires 25 main frames to be transmitted, and the transmission time of each main frame is 30 seconds. Therefore, it takes 750 seconds to transmit a complete navigation message.
- For terminal equipment in order to obtain a complete navigation message, it is necessary to continuously monitor the navigation message for more than 750 seconds. In the above process, on the one hand, the terminal device needs to continuously monitor the navigation message for a long time, so the overhead is high. On the other hand, in order for the terminal equipment to obtain the history of each satellite, it takes 750 seconds, which will also cause a large delay.
- FIG. 2 is a schematic diagram of the application scenario of GPS.
- the staff compiles navigation messages and enters the navigation messages into the ground master control station.
- the ground master control station transmits the navigation messages to the ground injection station, and the ground injection station Inject navigation messages into satellite storage systems.
- the satellite then broadcasts navigation messages to the terminal equipment in the above-mentioned manner.
- the terminal equipment interprets the navigation message and calculates the current position, speed and other information.
- precise positioning and satellite forecasting are required. Therefore, the terminal device needs to learn the ephemeris of the satellites and the almanacs of all satellites through navigation messages.
- the satellite's ephemeris includes time parameters, Kepler orbit parameters, and orbit perturbation parameters. Based on these parameters, the current observed satellite position can be obtained, thereby realizing the positioning of the terminal device.
- the almanac of all satellites includes the basic orbital parameters of all satellites. Based on these parameters, satellite forecasts can be made.
- Satellites can also be used in mobile communications with the continuous development of mobile communication technology.
- This kind of satellite-based mobile communication can be called satellite communication.
- Satellite communication like other mobile communication methods, needs to implement various services such as voice calls, video calls, and watching videos. Therefore, satellite communication systems need to maintain low latency and low overhead to ensure the normal operation of the above-mentioned services. run.
- the above-mentioned method of broadcasting the ephemeris and almanac of satellites through navigation messages in the above-mentioned GPS system is not suitable for use in satellite communication systems because of the large overhead and time delay.
- the terminal equipment obtains the ephemeris and almanac of the satellite, which is mainly used to determine the position information of the currently observed satellite, determine the topology of the satellite network according to the position information, and perform satellite overhead prediction. And then conduct business data interaction and so on.
- the accuracy of the satellite location information is relatively low, and the topology of the satellite network can still be determined when the accuracy of the location information is low. Therefore, for a satellite communication system, only necessary ephemeris parameters need to be obtained, and the position information of the currently observed satellites can be determined based on these parameters.
- the obtained position information can enable the terminal equipment to determine the topology of the satellite network.
- the positional relationship between the satellites is relatively fixed. Therefore, based on the position information of the currently observed satellites, the position information of other satellites in the satellite network can be obtained according to the position relationship between the satellites, and then the topology of the satellite network can be obtained.
- an embodiment of the application provides a communication method applied to a satellite communication system.
- the terminal device only obtains necessary ephemeris parameters, and according to the necessary ephemeris parameters, determines the position information of the currently observed satellite and the satellite Location information of other satellites in the network. According to the position information of the satellites currently observed and the position information of other satellites, the topology of the satellite network can be determined, and the satellite overhead prediction can be performed.
- FIG. 3 is a schematic diagram of an exemplary system architecture of the communication method provided by an embodiment of the application. It is worth noting that FIG. 3 is an example of the integration of a satellite network and a 5G network, but this is not a limitation to the embodiment of the application.
- the communication method provided in the embodiments of the present application can also be applied to a system where a satellite network is integrated with a 2G network, a 3G network, a 4G network, and the like.
- the satellite network and 5G network integration system includes: terminal equipment, 5G base stations deployed on the satellite, ground stations, and 5G core network.
- 5G base stations are deployed on the satellites of the satellite network, and communicate with the 5G core network on the ground through wireless links for signaling interaction and service data transmission. There are wireless links between the satellites, through which signaling interaction and user data transmission between 5G base stations can be realized.
- a terminal device may also be called a terminal, a user equipment (UE), a mobile station (mobile station, MS), a mobile terminal (mobile terminal, MT), and so on.
- the terminal device can be a mobile phone (mobile phone), a tablet computer (pad), a computer with wireless transceiver function, virtual reality (VR) terminal equipment, augmented reality (AR) terminal equipment, industrial control (industrial control) Control), wireless terminals in self-driving (self-driving), wireless terminals in remote medical surgery, wireless terminals in smart grid (smart grid), transportation safety (transportation safety) Wireless terminal, wireless terminal in smart city, wireless terminal in smart home, etc.
- the terminal equipment communicates with the 5G base station deployed on the satellite through the 5G new air interface.
- 5G base stations are mainly used to provide wireless access services and schedule wireless resources for use by connected terminal devices. At the same time, 5G base stations also provide reliable wireless transmission protocols and data encryption protocols.
- the deployment in the satellite can also be the global system for mobile communication (GSM) or code division multiple access (GSM).
- GSM global system for mobile communication
- GSM code division multiple access
- the base transceiver station (BTS) in code division multiple access (CDMA) can also be the base station (NodeB) in wideband code division multiple access (WCDMA), or it can be an evolved type in LTE Base station (eNB or e-NodeB, evolutional Node B), etc.
- a wireless link can be established between 5G base stations and 5G base stations through the Xn interface.
- the 5G core network is used for services such as user access control, mobility management, session management, user security authentication, and billing.
- the 5G core network is composed of multiple functional units, which can be divided into functional entities of the control plane and functional entities of the user plane.
- the control plane functional entities mainly include access and mobility management function (AMF) and session management function (session management function, SMF).
- the user plane function entity mainly includes the user plane function (UPF).
- AMF is responsible for user access, security authentication and mobility management
- SMF provides service continuity and uninterrupted user experience of services.
- UPF is responsible for the management of user plane data transmission, traffic statistics, and security eavesdropping.
- the above-mentioned 5G core network can be replaced with the core network of 2G network, the core network of 3G network, and the core network of 4G network.
- a wireless link can be established between the 5G core network and the 5G base station through the NG interface.
- the following embodiments of the present application mainly relate to the interaction process between the above-mentioned terminal equipment and the satellite deployed with the 5G base station.
- the ephemeris of the satellite includes time parameters, Kepler orbit parameters, and orbit perturbation parameters. Based on these parameters, the precise position of the currently observed satellite can be obtained.
- the time parameter includes the ephemeris reference time t 0e
- the Kepler orbit parameter includes: the square root of the semi-major axis of the orbit
- the orbital perturbation parameters include: correction value of the perigee angle, right ascension of the ascending node
- the terminal device can determine the position information of the currently observed satellite and the position information of other satellites in the satellite network.
- Figure 4 is a schematic diagram of satellite orbit parameters
- Figure 5 is a schematic diagram of satellite orbit parameters.
- the orbit semi-major axis a and the orbit eccentricity are determined by the satellite network. Therefore, the orbit half-length Axis square root And eccentricity e will not change.
- Perigee angular distance refers to the angle between the ascending node and the perigee in the orbital plane. Therefore, the perigee angular distance ⁇ will not change.
- the orbital surface inclination i 0 and the ascending node right ascension ⁇ 0 at the reference time are also determined by the satellite network.
- the mean anomaly angle M 0 at the reference time is a function of time. This parameter determines the instantaneous position of the satellite in the orbit. Therefore, this parameter will change with the reference time.
- Such a satellite network may be, for example, the Walker constellation.
- the Walker constellation As an example, it has the characteristics of a circular orbit, the same inclination of the orbital surface, evenly spaced ascending nodes of the orbital surface, evenly spaced satellites in the orbit, and equal phase spacing between adjacent orbital surfaces.
- the terminal device can obtain these parameters in a specific way, and store these parameters in the terminal device. When the terminal device needs to determine the position information of the satellite, it can be used directly. These parameters are transmitted every time without the satellite.
- the ephemeris reference time t 0e and the reference time mean anomaly angle M 0 in the above-mentioned necessary ephemeris parameters will change during the operation of the satellite, so they can be sent to the terminal equipment by the satellite, and the terminal equipment according to the current
- the ephemeris reference time t 0e and the mean anomaly angle M 0 of the reference time sent by the observed satellites, as well as the above parameters determined by the satellite network that will not change, can determine the currently observed satellite and its satellites in the satellite network Position information, and then get the topology of the satellite network.
- the terminal device can be based on the aforementioned ephemeris reference time t 0e and the square root of the orbit semi-major axis in the Kepler orbit parameter
- the eccentricity e, the angular distance of perigee ⁇ , the inclination of the orbital plane at the reference moment i 0 , the ascension of the ascending node ⁇ 0 , the mean anomaly at the reference moment M 0 , the current observation is derived using the following formulas (1) to (12)
- the position information of the arrived satellite, the position information is the position coordinates (X k , Y k , Z k ).
- the position information of the satellite currently observed by formula (12), the position information is the position coordinates (X k , Y k , Z k )
- each Satellites are distributed at equal intervals in the same orbital plane. Therefore, based on calculating the position information of the currently observed satellites, according to the positional interval between the satellites distributed on the orbital plane, the positions of other satellites in the same orbital plane can be calculated. location information.
- the different orbital planes of these satellite networks are also distributed at equal intervals. Therefore, based on the calculation of the position information of the satellites in one orbital plane, other orbital planes can be calculated based on the position interval between the orbital planes. The position information of the satellites within the network, thereby obtaining the satellite network topology.
- the terminal device can obtain it in either of the following two ways:
- the ephemeris parameters that will not change are stored in the terminal device.
- the satellite when the terminal device accesses the network for the first time, the satellite sends the ephemeris parameters that will not change to the terminal device, and the terminal device stores it.
- the terminal device's first network access may mean that the terminal device accesses the network through a random access process, or it may mean that the terminal device switches from one network to another network.
- the terminal device can obtain it in either of the following two ways:
- the satellite broadcasts the changing ephemeris parameters to the terminal device according to a preset period.
- the terminal device when the terminal device needs to use the ephemeris parameters to determine the topology of the satellite network, it requests the satellite to send the ephemeris parameters that will change.
- FIG. 6 is an interaction flowchart of Embodiment 1 of the communication method provided by an embodiment of the application. As shown in FIG. 6, the interaction process between the terminal device and the satellite includes:
- the satellite sends a master information block (master information block, MIB) to the terminal device.
- MIB master information block
- the MIB includes basic information about the terminal device accessing the network, and through this information, the terminal device can learn the remaining minimum system information (RMSI) receiving mode.
- RMSI remaining minimum system information
- the satellite sends the RMSI to the terminal device.
- the terminal device After the terminal device learns the RMSI receiving mode, it receives the RMSI sent by the satellite according to the receiving mode.
- the RMSI carries the necessary information for the terminal device to access the network, including the uplink initial bandwidth part (BWP), the channel configuration in the initial BWP, and the semi-static ratio of the cell.
- BWP uplink initial bandwidth part
- the channel configuration in the initial BWP the channel configuration in the initial BWP
- the semi-static ratio of the cell the semi-static ratio of the cell.
- the satellite sends a first system message to the terminal device, where the first system message is used to indicate the mean anomaly of the currently observed satellite at the ephemeris reference moment.
- the satellite interacting with the terminal device is the satellite currently observed by the terminal device, and the currently observed satellite may be referred to as the first satellite.
- the “ephemeris reference moment” may be referred to as “reference moment” for short in the embodiments of the present application.
- the mean anomaly angle of the satellite at the reference moment represents the mean anomaly angle of the satellite at the ephemeris reference moment.
- the above-mentioned first system message may carry the ephemeris reference time t 0e and the reference time mean anomaly M 0 in the above-mentioned necessary ephemeris parameters, and at the same time, the first system message carries the identification of the satellite currently observed by the terminal device .
- the terminal device can know which satellite in the satellite network is currently observed according to the satellite's identifier, and the terminal device can know which satellite in the satellite network is currently observed according to the ephemeris reference time t 0e and the reference time average anomaly angle M 0 The satellite's mean anomaly angle M 0 at time t 0e .
- the remaining necessary ephemeris parameters that will not change are all pre-stored in the terminal device.
- the method for the terminal device to pre-store the remaining ephemeris parameters that will not change may be the foregoing terminal device pre-stored when it leaves the factory, or the foregoing terminal device may be sent to the terminal device by the satellite when the terminal device first enters the network.
- the system message may include MIB and system information blocks (system information blocks, SIB).
- SIB system information blocks
- the SIB may be extended, and the extended SIB may be used as the first system message described above, and the ephemeris reference is carried in the message.
- the time t 0e , the mean anomaly angle M 0 at the reference time and the identifier of the satellite are used to indicate the mean anomaly angle of the currently observed satellite at the reference time.
- the ephemeris reference time t 0e carried in the first system message can be 16 bits, and the value range can be 0 degrees to 360 degrees, and the reference time mean anomaly angle M 0 can be 32 bits, and the unit is seconds.
- the satellite ID can be 16 bits, and the value range can be 0 to 65535.
- the terminal device determines the topology of the satellite network according to the first system message and pre-stored ephemeris parameters that will not change.
- the satellite may broadcast the foregoing first system message according to a preset period.
- the specific determination method can refer to the description in the foregoing using formula (1) to determine the position information of the satellite and then determine the topology of the satellite network, which will not be repeated here.
- the terminal device receives the first system message sent by the satellite according to the preset period.
- the system message is used to indicate the mean anomaly of the currently observed satellite at the reference moment, based on the first system message and the terminal device pre-stored With the ephemeris parameters that will not change, the terminal device can determine the currently observed satellites and the position information of other satellites in the satellite network, and then can obtain the satellite network topology. Since the first system message is only used to indicate the mean anomaly angle of the currently observed satellite at the reference moment, that is, the first system message only needs to carry fewer parameters. Therefore, the terminal device only needs less time delay and smaller The overhead of the satellite network can be determined, so that the satellite communication system can meet the requirements of low delay and low overhead.
- the satellite actively broadcasts the first system message periodically according to a preset period.
- the satellite sends the above-mentioned first system message to the terminal device after receiving the request message from the terminal device.
- FIG. 7 is an interaction flowchart of Embodiment 2 of the communication method provided by an embodiment of the application. As shown in FIG. 7, the interaction process between the terminal device and the satellite includes:
- the satellite sends the MIB to the terminal device.
- step S601 The execution process of this step is the same as the aforementioned step S601, and the aforementioned step S601 can be referred to, which will not be repeated here.
- the satellite sends the RMSI to the terminal device.
- step S602 The execution process of this step is the same as the aforementioned step S602, and you can refer to the aforementioned step S602, which will not be repeated here.
- the terminal device sends a first request message to the satellite.
- the first request message is used to request the satellite to send a first system message indicating the mean anomaly of the currently observed satellite at the reference moment.
- the first request message may be a system message, such as a SIB message.
- a timer may be set in the terminal device, and the sending of the foregoing first request message may be controlled by the timer.
- the initial value of the timer can be indicated by the network device to the terminal device when the terminal device is successfully registered in the network.
- the terminal device initiates a registration request to the core network, and when the core network returns a Registration Accept message indicating that the registration is successful to the terminal device, the Registration Accept message carries the initial value of the timer.
- the timer controls the sending of the above-mentioned first request message as follows:
- the timer resets the initial value and starts timing.
- the terminal device When the timer expires, the terminal device is triggered to send the above-mentioned first request message to the satellite to request the satellite to send the first system message, and at the same time, the terminal device terminates the timer.
- the timer expires.
- the satellite sends a first system message to the terminal device, where the first system message is used to indicate the mean anomaly of the currently observed satellite at the reference moment.
- step S603 The execution process of this step is the same as the aforementioned step S603, and you can refer to the aforementioned step S603, which will not be repeated here.
- the terminal device determines the topology of the satellite network according to the first system message and pre-stored ephemeris parameters that will not change.
- step S604 The execution process of this step is the same as the aforementioned step S604, and the aforementioned step S604 can be referred to, which will not be repeated here.
- the terminal device actively sends a first request message to the satellite, and the satellite sends a first system message to the terminal device according to the first request message.
- the first system message is used to indicate the current observation of the satellite at the reference moment.
- the average anomaly based on the first system message and the ephemeris parameters stored in advance by the terminal device that will not change, the terminal device can determine the currently observed satellite and the position information of other satellites in the satellite network, and then obtain the satellite network Topology. Since the first system message is only used to indicate the mean anomaly angle of the currently observed satellite at the reference moment, that is, the first system information only needs to carry fewer parameters. Therefore, the terminal only needs less time delay and smaller
- the overhead can determine the topology of the satellite network, which can meet the requirements of low delay and low overhead of the satellite communication system.
- the first system message is used to indicate the mean anomaly of the currently observed satellite at the reference time.
- the first system message can carry the ephemeris reference time t 0e and the reference Mean anomaly at time M 0 , the identification of the currently observed satellite.
- the first system message may also carry the identification of the currently latest online satellite and/or the identification of the currently latest offline satellite.
- a satellite list can be stored on the terminal device, and the satellites in the satellite list are the satellites that are currently online.
- the terminal device can select a suitable satellite for communication according to the list of satellites to initiate service requests and obtain user data.
- the operating status of some satellites in the satellite network changes, for example, a satellite has just joined the satellite network, a satellite has changed from offline to online, or a satellite has changed from online to offline due to failure or energy saving
- the satellite list stored on the terminal device is not updated synchronously, it may cause the terminal device to fail to send messages normally and other consequences.
- the above-mentioned first system message can be used to carry the ephemeris reference time t 0e , the reference time mean anomaly angle M 0 , and the identification of the currently observed satellite in the first system message. , It can also carry the ID of the latest online satellite and/or the ID of the latest offline satellite.
- the terminal device After receiving the first system message, the terminal device can update the locally stored satellite list according to the latest online satellite identification and/or the latest offline satellite identification carried by it, so that the satellites in the locally stored satellite list The operating state of the device is consistent with the actual operating state, thereby ensuring that the terminal device can communicate with the satellite normally.
- the terminal device receives the first system message from the satellite, and the first system message carries the ephemeris reference time t 0e , the reference time mean anomaly angle M 0 , and the identifier of the currently observed satellite, that is, the The first system message only carries the necessary ephemeris parameters that will change, and the remaining ephemeris parameters that will not change are pre-stored locally by the terminal device.
- the ephemeris parameters that will not change at the factory can be stored in the terminal device, or the ephemeris parameters that will not change when the terminal device enters the network for the first time can also be stored in the terminal device.
- the following describes the process of storing the ephemeris parameters that will not change in the terminal device when the terminal device enters the network for the first time.
- FIG. 8 is an interaction flowchart of Embodiment 3 of the communication method provided by an embodiment of the application.
- the satellite interacting with the terminal device in the following process is called the second satellite, and the second satellite is the satellite observed by the terminal device when it first accesses the network.
- the second satellite and the aforementioned first satellite may be the same satellite or different satellites.
- the interaction process between the terminal equipment and the satellite includes:
- the satellite sends the MIB to the terminal device.
- the MIB includes the basic information of the terminal device accessing the network. Through this information, the terminal device can learn the receiving mode of RMSI.
- the satellite sends the RMSI to the terminal device.
- the terminal device After the terminal device learns the RMSI receiving mode, it receives the RMSI sent by the satellite according to the receiving mode.
- the RMSI carries the necessary information for the terminal equipment to access the network, including the initial uplink BWP, the channel configuration in the initial BWP, and the semi-static ratio of the cell.
- S803 The terminal device sends a second request message to the satellite.
- the second request message is used to request the satellite to send a second system message indicating the ephemeris parameter of the satellite.
- the first request message may be a system message, such as a SIB message.
- the terminal device accesses the network for the first time, it is determined whether the satellite ephemeris parameters are saved on the terminal device. If not, the terminal device sends the second request message to the satellite through this step after receiving the RMSI sent by the satellite To request the satellite to send the second system message.
- S804 The satellite sends the second system message to the terminal device.
- the second system message is used to indicate the ephemeris parameters of the satellite.
- the second system message can carry the square root of the semi-major axis of the orbit that will not change The eccentricity e, the perigee angular distance ⁇ , the orbital surface inclination at the reference time i 0 , and the right ascension of the ascending node ⁇ 0 .
- the terminal device After the terminal device reads these parameters from the second system message, it stores these parameters in the terminal device. After the terminal device enters the network and before exiting from the network, the terminal device can directly use these parameters.
- the second system message may also carry the ephemeris reference time t 0e , the reference time mean anomaly angle M 0 , and the identifier of the currently observed satellite.
- the identifier of the currently observed satellite is the identifier of the second satellite, and the ephemeris reference time t 0e and the reference time mean anomaly angle M 0 have the same meaning as in the foregoing first system message, and will not be repeated here.
- the terminal device can determine the topology of the satellite network when it enters the network. On this basis, the terminal device can continuously obtain the ever-changing ephemeris reference time t 0e and the mean anomaly angle M 0 of the reference time based on the foregoing embodiment, and continuously obtain the updated topology of the satellite network.
- the aforementioned second system message may also carry specific network parameters of the satellite network.
- the above second system message may also carry the following specific parameters of the Walker constellation:
- the number of satellites on each orbital plane the number of constellation orbital planes, and the phase difference between adjacent orbital planes.
- the identification of the satellite after calculating the position information of the currently observed satellite using the method described above, according to the number of satellites on each orbital plane in the above-mentioned unique parameters, the position of each satellite in an orbital plane in the satellite network can be determined The interval, and then according to the position interval of each satellite, the position information of other satellites in the same orbit can be calculated.
- the positional interval between the orbital planes of the satellite network can be determined, and further, according to the positional interval between the orbital planes, it can be calculated Position information of satellites in other orbital planes to get the topology of the satellite network
- the foregoing second system message may also carry an identifier of a satellite that is currently online.
- the terminal device can generate the satellite list described above according to the identification of the satellite that is currently online. In the subsequent operation process, the terminal device can select a suitable satellite from the satellite list for communication to initiate service requests and obtain user data.
- the foregoing second system message may be SIB.
- the terminal device determines the topology of the satellite network according to the second system message.
- the specific determination method can refer to the description in the foregoing using formula (1) to determine the position information of the satellite and then determine the topology of the satellite network, which will not be repeated here.
- the terminal device sends a second request message to the satellite when it enters the network for the first time, and the satellite sends a second system message to the terminal device according to the second request message.
- the second system message carries necessary ephemeris parameters of the satellite.
- the terminal equipment can determine the position information of the currently observed satellite and other satellites in the satellite network, and then can obtain the topology of the satellite network.
- the terminal device obtains and saves the necessary ephemeris parameters that will not change through the second system message when it enters the network for the first time. Before exiting the network, the terminal device can directly use these parameters without obtaining it from the satellite, thereby reducing the delay And overhead, meeting the requirements of low delay and low overhead in satellite communication systems.
- FIG. 9 is a module structure diagram of a satellite communication device provided by an embodiment of the application.
- the device may be the terminal device described in the foregoing embodiment, or it may be a terminal that can support the terminal device to implement the method provided in the embodiment of the application.
- the functional device of the device for example, the device may be a device or a chip system in a terminal device. As shown in Figure 9, the device includes:
- the receiving module 901 is configured to receive a first system message sent by a first satellite, where the first system message is used to indicate the mean anomaly of the first satellite at the ephemeris reference moment.
- the processing module 902 is configured to determine the topology of the satellite network to which the first satellite belongs according to the first system message.
- the first system message includes the identity of the first satellite, the ephemeris reference time, and the mean anomaly of the first satellite at the ephemeris reference time.
- the above-mentioned first system message further includes an identifier of a satellite that is currently online and/or an identifier of a satellite that is currently offline.
- the foregoing apparatus further includes:
- the sending module 903 is configured to send a first request message to the first satellite, where the first request message is used to request the first satellite to send the first system message.
- the sending module 903 is configured to send a second request message to the second satellite, where the second request message is used to request to obtain the ephemeris parameter of the second satellite.
- the receiving module 901 is further configured to receive a second system message sent by the second satellite, and the second system message is used to indicate the ephemeris parameter of the second satellite.
- the second system message includes the square root of the semi-major axis of the orbit of the satellite network, the eccentricity, the angular distance of perigee, the inclination of the orbit at the reference time, and the right ascension of the ascending node.
- the second system message further includes the identifier of the second satellite, the ephemeris reference time, and the mean anomaly of the second satellite at the ephemeris reference time.
- FIG. 10 is a module structure diagram of another satellite communication device provided by an embodiment of this application.
- the device may be the satellite described in the foregoing embodiment, or it may be capable of supporting satellites to implement the satellite in the method provided in the embodiments of this application.
- a functional device for example, the device may be a device in a satellite or a chip system. As shown in Figure 10, the device includes:
- the processing module 1001 is configured to send a first system message to the terminal device through the sending module 1002, so that the terminal device determines the topology of the satellite network to which the first satellite belongs according to the first system message, wherein the first system message is used to indicate The mean anomaly of the first satellite at the ephemeris reference moment.
- the first system message includes the identity of the first satellite, the ephemeris reference time, and the mean anomaly of the first satellite at the ephemeris reference time.
- the above-mentioned first system message further includes an identifier of a satellite that is currently online and/or an identifier of a satellite that is currently offline.
- the foregoing apparatus further includes:
- the receiving module 1003 is configured to receive a first request message sent by the terminal device, where the first request message is used to request the first satellite to send the first system message.
- the sending module 1002 is specifically configured to send the above first system message to the terminal device according to the above first request message.
- the receiving module 1003 is configured to receive a second request message sent by the aforementioned terminal device, and the second request message is used to request to obtain the ephemeris parameter of the second satellite.
- the sending module 1002 is further configured to send a second system message to the terminal device according to the second request message, where the second system message is used to indicate the ephemeris parameter of the second satellite.
- the second system message includes the square root of the semi-major axis of the orbit of the satellite network, the eccentricity, the angular distance of perigee, the inclination of the orbit at the reference time, and the right ascension of the ascending node.
- the second system message further includes the identifier of the second satellite, the ephemeris reference time, and the mean anomaly of the second satellite at the ephemeris reference time.
- the satellite communication device provided in the embodiment of the present application can execute the method steps in the above method embodiment, and its implementation principles and technical effects are similar, and will not be repeated here.
- the division of the various modules of the above device is only a division of logical functions, and may be fully or partially integrated into a physical entity in actual implementation, or may be physically separated.
- these modules can all be implemented in the form of software called by processing elements; they can also be implemented in the form of hardware; some modules can be implemented in the form of calling software by processing elements, and some of the modules can be implemented in the form of hardware.
- the determining module may be a separately established processing element, or it may be integrated into a certain chip of the above-mentioned device for implementation.
- each step of the above method or each of the above modules can be completed by hardware integrated logic circuits in the processor element or instructions in the form of software.
- the above modules may be one or more integrated circuits configured to implement the above methods, such as one or more application specific integrated circuit (ASIC), or one or more microprocessors (digital signal processor, DSP), or, one or more field programmable gate arrays (FPGA), etc.
- ASIC application specific integrated circuit
- DSP digital signal processor
- FPGA field programmable gate arrays
- the processing element may be a general-purpose processor, such as a central processing unit (CPU) or other processors that can call program codes.
- CPU central processing unit
- these modules can be integrated together and implemented in the form of a system-on-a-chip (SOC).
- SOC system-on-a-chip
- the above embodiments it may be implemented in whole or in part by software, hardware, firmware or any combination thereof.
- software it can be implemented in the form of a computer program product in whole or in part.
- the computer program product includes one or more computer instructions.
- the processes or functions described in the embodiments of the present application are generated in whole or in part.
- the above-mentioned computer may be a general-purpose computer, a special-purpose computer, a computer network, or other programmable devices.
- the above-mentioned computer instructions can be stored in a computer-readable storage medium, or transmitted from one computer-readable storage medium to another computer-readable storage medium.
- the above-mentioned computer instructions can be transmitted from a website, computer, server, or data center through a cable (Such as coaxial cable, optical fiber, digital subscriber line (DSL)) or wireless (such as infrared, wireless, microwave, etc.) to another website site, computer, server or data center.
- a cable such as coaxial cable, optical fiber, digital subscriber line (DSL)
- wireless such as infrared, wireless, microwave, etc.
- the foregoing computer-readable storage medium may be any available medium that can be accessed by a computer or a data storage device such as a server or data center integrated with one or more available media.
- the above-mentioned usable medium may be a magnetic medium (for example, a floppy disk, a hard disk, and a magnetic tape), an optical medium (for example, a DVD), or a semiconductor medium (for example, a solid state disk (SSD)).
- a magnetic medium for example, a floppy disk, a hard disk, and a magnetic tape
- an optical medium for example, a DVD
- a semiconductor medium for example, a solid state disk (SSD)
- an embodiment of the present application also provides a satellite communication device for implementing the satellite communication method in the foregoing embodiment. Part or all of can be implemented by hardware or software.
- the satellite communication device 1100 includes:
- the input interface circuit 1102, the logic circuit 1104, and the output interface circuit 1106 also include a transceiver 1108 and an antenna 1110.
- the transceiver 1108 transmits and receives data through the antenna 1110.
- the logic circuit 1104 is used to execute the method steps of the terminal device or the satellite in the satellite communication method shown in FIG. 6 to FIG. 8.
- the aforementioned satellite communication device 1100 may be a chip or an integrated circuit.
- FIG. 12 is a schematic structural diagram of a terminal device provided by an embodiment of this application.
- the terminal device 1200 may include: a processor 121 (for example, a CPU), a memory 122, and a transceiver 123; the transceiver 123 is coupled to the processor 121, and the processor 121 controls the transceiver 123's transceiving actions.
- Various instructions may be stored in the memory 122 to complete various processing functions and implement method steps executed by the terminal device in the embodiments of the present application.
- the terminal device involved in the embodiment of the present application may further include: a power supply 124, a system bus 125, and a communication port 126.
- the transceiver 123 may be integrated in the transceiver of the terminal device, or may be an independent transceiver antenna on the terminal device.
- the system bus 125 is used to implement communication connections between components.
- the aforementioned communication port 126 is used to implement connection and communication between the terminal device and other peripherals.
- the above-mentioned processor 121 is configured to couple with the memory 122 to read and execute the instructions in the memory 122 to implement the method steps executed by the terminal device in the above-mentioned method embodiment.
- the transceiver 123 is coupled with the processor 121, and the processor 121 controls the transceiver 123 to send and receive messages.
- the implementation principles and technical effects are similar, and will not be repeated here.
- the system bus mentioned in FIG. 12 may be a peripheral component interconnection standard (PCI) bus or an extended industry standard architecture (EISA) bus.
- PCI peripheral component interconnection standard
- EISA extended industry standard architecture
- the system bus can be divided into address bus, data bus, control bus, etc. For ease of representation, only one thick line is used in the figure, but it does not mean that there is only one bus or one type of bus.
- the communication interface is used to realize the communication between the database access device and other devices (such as client, read-write library and read-only library).
- the memory may include random access memory (RAM), and may also include non-volatile memory (non-volatile memory), such as at least one disk memory.
- the above-mentioned processor can be a general-purpose processor, including a central processing unit CPU, a network processor (NP), etc.; it can also be a digital signal processor DSP, an application specific integrated circuit ASIC, a field programmable gate array FPGA or other Programming logic devices, discrete gates or transistor logic devices, discrete hardware components.
- a general-purpose processor including a central processing unit CPU, a network processor (NP), etc.; it can also be a digital signal processor DSP, an application specific integrated circuit ASIC, a field programmable gate array FPGA or other Programming logic devices, discrete gates or transistor logic devices, discrete hardware components.
- FIG. 13 is a schematic structural diagram of a satellite provided by an embodiment of this application.
- the satellite 1300 may include: a processor 131 (for example, a CPU), a memory 132, and a transceiver 133; the transceiver 133 is coupled to the processor 131, and the processor 131 controls the transceiver 133 to send and receive actions.
- Various instructions can be stored in the memory 132 to complete various processing functions and implement the method steps executed by the satellite in the embodiment of the present application.
- the satellite involved in the embodiment of the present application may further include: a power supply 134, a system bus 135, and a communication port 136.
- the transceiver 133 may be integrated in the satellite transceiver, or may be an independent transceiver antenna on the satellite.
- the system bus 135 is used to implement communication connections between components.
- the aforementioned communication port 136 is used to realize connection and communication between the satellite and other peripherals.
- the aforementioned processor 131 is configured to couple with the memory 132, read and execute instructions in the memory 132, so as to implement the method steps executed by the satellite in the aforementioned method embodiment.
- the transceiver 133 is coupled with the processor 131, and the processor 131 controls the transceiver 123 to send and receive messages.
- the implementation principles and technical effects are similar, and will not be repeated here.
- the system bus mentioned in FIG. 12 may be a PCI bus or an EISA bus.
- the above system bus can be divided into address bus, data bus, control bus and so on. For ease of representation, only one thick line is used in the figure, but it does not mean that there is only one bus or one type of bus.
- the communication interface is used to realize the communication between the database access device and other devices (such as client, read-write library and read-only library).
- the memory may include RAM, or may also include non-volatile memory, such as at least one disk memory.
- the aforementioned processor may be a general-purpose processor, including CPU, NP, etc.; it may also be a DSP, ASIC, FPGA or other programmable logic device, discrete gate or transistor logic device, or discrete hardware component.
- an embodiment of the present application further provides a computer-readable storage medium that stores instructions in the storage medium, which when run on a computer, causes the computer to execute the satellite processing process or terminal device processing in the foregoing embodiment process.
- an embodiment of the present application further provides a chip for executing instructions, and the chip is used to execute the processing procedure of the satellite or the processing procedure of the terminal device in the foregoing embodiment.
- the embodiment of the present application also provides a program product, the program product includes a computer program, the computer program is stored in a storage medium, at least one processor can read the computer program from the storage medium, and the at least one processor executes the above implementation In the example, the processing procedure of the satellite or the processing procedure of the terminal equipment.
- At least one refers to one or more, and “multiple” refers to two or more.
- “And/or” describes the association relationship of the associated objects, indicating that there can be three relationships, for example, A and/or B, which can mean: A alone exists, both A and B exist, and B exists alone, where A, B can be singular or plural.
- the character “/” generally indicates that the associated objects before and after are in an “or” relationship; in the formula, the character “/” indicates that the associated objects before and after are in a “division” relationship.
- “The following at least one item (a)” or similar expressions refers to any combination of these items, including any combination of a single item (a) or plural items (a).
- at least one of a, b, or c can mean: a, b, c, ab, ac, bc, or abc, where a, b, and c can be single or multiple One.
- the size of the sequence numbers of the foregoing 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 be implemented in this application.
- the implementation process of the example constitutes any limitation.
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Abstract
本申请实施例提供一种卫星通信方法、装置、终端设备、卫星及可读存储介质,在该方法中,终端设备接收第一卫星发送的第一***消息,该第一***消息用于指示第一卫星在星历参考时刻的平近点角。终端设备接收到该第一***消息后,根据该第一***消息,可以确定第一卫星所属卫星网络的拓扑。该方法使得终端仅需要较少的时延和较小的开销,即可确定出卫星网络的拓扑,因而可以满足卫星通信***时延低、开销小的要求。
Description
本申请要求于2019年07月08日提交国家知识产权局、申请号为201910609440.X、申请名称为“卫星通信方法、装置、终端设备、卫星及可读存储介质”的中国专利申请的优先权,其全部内容通过引用结合在本申请中。
本申请实施例涉及通信技术,尤其涉及一种卫星通信方法、装置、终端设备、卫星及可读存储介质。
全球移动通信是移动通信的重要发展方向,卫星通信是实现全球移动通信的重要手段。卫星通信是利用人造地球卫星作为中继站来转发无线电波而进行的两个或多个终端设备之间的通信。相比于地面通信,卫星通信具有覆盖范围广、通信容量大、传输质量好、组网方便迅速、便于实现全球无缝链接等优点。使用卫星通信,能够使得用户在全球任何区域范围内,均可以进行语音通话、视频通话、观看视频等各项业务。在卫星通信中,如何实现卫星与终端设备之间的信息交互,使得终端设备及时获知卫星的星历数据,是重要的研究课题。
传统技术中涉及的卫星与终端设备的信息交互方法主要为全球定位***(global positioning system,GPS)中卫星与终端设备的交互方法。在GPS中,卫星通过导航电文将卫星的星历数据发送给终端设备。终端设备根据从导航电文中获取的星历数据,选择适当的卫星并捕获所选择的卫星。导航电文每帧的长度为30秒/1500比特,终端设备为了获取完整的星历数据,需要持续监听导航电文750秒以上。
但是,传统的方式中终端设备获取卫星的星历数据的耗时较长,开销较大,无法适应卫星通信中开销小、时延低的要求。
发明内容
本申请实施例提供一种卫星通信方法、装置、终端设备、卫星及可读存储介质,能够适应卫星通信中开销小、时延低的要求。
第一方面,本申请实施例提供一种卫星通信方法,在该方法中,终端设备接收第一卫星发送的第一***消息,该第一***消息用于指示第一卫星在星历参考时刻的平近点角。终端设备接收到该第一***消息后,根据该第一***消息,可以确定第一卫星所属卫星网络的拓扑。
在上述方法中,终端设备接收卫星按照预设周期发送的第一***消息,该***消息用于指示当前观测到的卫星在参考时刻的平近点角,基于第一***消息以及终端设备预先存储的不会发生改变的星历参数,终端设备可以确定出当前观测到的卫星以及卫星网络中其他卫星的位置信息,进而可以得到卫星网络的拓扑。由于第一***消息仅用于指示当前观测到的卫星在参考时刻的平近点角,即第一***信息只需要携带较少的参数,因此,终端设备仅需要较少的时延和较小的开销,即可确定出卫星网络的拓扑,因而可以满足卫星通信***时延低、开销小的要求。
在一种可能的实现方式中,第一***消息中可以包括第一卫星标识、星历参考时刻以及所述第一卫星在所述星历参考时刻的平近点角。通过这些参数,可以得到第一卫星在在星历参考时刻的平近点角。
在一种可能的实现方式中,第一***消息中还可以包括当前上线的卫星的标识和/或当前离线的卫星的标识。
通过在第一***消息中携带当前上线的卫星的标识和/或当前离线的卫星的标识,可以使得终端设备根据其所携带的最新上线的卫星的标识和/或最新离线的卫星的标识,更新本地存储的卫星列表,从而使得本地存储的卫星列表中的卫星的运行状态与实际的运行状态一致,进而保证终端设备可以与卫星进行正常通信。
在一种可能的实现方式中,终端设备可以向第一卫星发送第一请求消息,该第一请求消息用于请求所述第一卫星发送所述第一***消息。第一卫星根据该第一请求消息,向终端设备发送第一***消息。
在该方式中,由终端设备主动向第一卫星请求第一***消息。
作为另一种可能的实现方式,还可以由第一卫星按照预设的周期主动发送上述第一请求消息。
在一种可选的实现方式中,终端设备可以通过定时器控制第一请求消息的发送。其中,该定时器的初始值可以在终端设备在网络中注册成功时,由网络设备向终端设备指示。当终端设备接收到第一***消息后,该定时器重置初始值,并开始计时。当该定时器过期后,触发终端设备向卫星发送上述第一请求消息,以请求卫星发送第一***消息,同时,终端设备终止定时器。当终端设备从网络中注销时,定时器终止。
在一种可选的实现方式中,在接收第一卫星发送的第一***消息之前,终端设备可以向第二卫星发送第二请求消息,该第二请求消息用于请求获取所述第二卫星的星历参数,进而,终端设备接收第二卫星发送的第二***消息,该第二***消息用于指示上述第二卫星的星历参数。
上述第二卫星与上述第一卫星可以为同一卫星,也可以为不同的卫星。
终端设备可以在首次入网时向第二卫星发送第二请求消息,并接收第二卫星发送的第二***消息。
在一种可选的实现方式中,上述第二***消息中包括所述卫星网络的轨道半长轴平方根、偏心率、近地点角距、参考时刻的轨道面倾角、升交点赤经。
在一种可选的上述所述第二***消息中还包括所述第二卫星的标识、星历参考时刻以及所述第二卫星在所述星历参考时刻的平近点角。
第二方面,本申请实施例提供一种卫星通信方法,在该方法中,第一卫星向终端设备发送第一***消息,以使终端设备根据该第一***消息确定第一卫星所属卫星网络的拓扑,其中,上述第一***消息用于指示上述第一卫星在星历参考时刻的平近点角。
在一种可选的实现方式中,上述第一***消息中包括上述第一卫星的标识、星历参考时刻以及上述第一卫星在上述星历参考时刻的平近点角。
在一种可选的实现方式中,上述第一***消息中还包括当前上线的卫星的标识和/或当前离线的卫星的标识。
在一种可选的实现方式中,第一卫星在向终端设备发送第一***消息之前,还可以接收终端设备发送的第一请求消息,该第一请求消息用于请求上述第一卫星发送上述第一***消息。第一卫星在接收到第一请求消息之后,根据上述第一请求消息,向终端设备发送上述第 一***消息。
在该方式中,第一卫星根据终端设备的请求发送第一***消息。
作为另一种可能的实现方式,还可以由第一卫星按照预设的周期主动发送上述第一请求消息。
在一种可选的实现方式中,第一卫星还可以接收上述终端设备发送的第二请求消息,该第二请求消息用于请求获取第二卫星的星历参数,并根据上述第二请求消息,向所述终端设备发送第二***消息,所述第二***消息用于指示所述第二卫星的星历参数。
在该方法中,第二卫星与第一卫星为同一卫星。
在一种可选的实现方式中,上述第二***消息中包括上述卫星网络的轨道半长轴平方根、偏心率、近地点角距、参考时刻的轨道面倾角、升交点赤经。
在一种可选的实现方式中,上述第二***消息中还包括上述第二卫星的标识、星历参考时刻以及上述第二卫星在上述星历参考时刻的平近点角。
第三方面,本申请实施例提供一种卫星通信装置,该装置包括:
接收模块,用于接收第一卫星发送的第一***消息,所述第一***消息用于指示所述第一卫星在星历参考时刻的平近点角;处理模块,用于根据所述第一***消息,确定所述第一卫星所属卫星网络的拓扑。
在一种可选的实现方式中,所述第一***消息中包括所述第一卫星的标识、星历参考时刻以及所述第一卫星在所述星历参考时刻的平近点角。
在一种可选的实现方式中,所述第一***消息中还包括当前上线的卫星的标识和/或当前离线的卫星的标识。
在一种可选的实现方式中,所述装置还包括:
发送模块,用于向所述第一卫星发送第一请求消息,所述第一请求消息用于请求所述第一卫星发送所述第一***消息。
在一种可选的实现方式中,所述装置还包括:
发送模块,用于向第二卫星发送第二请求消息,所述第二请求消息用于请求获取所述第二卫星的星历参数;所述接收模块,还用于接收第二卫星发送的第二***消息,所述第二***消息用于指示所述第二卫星的星历参数。
在一种可选的实现方式中,所述第二***消息中包括所述卫星网络的轨道半长轴平方根、偏心率、近地点角距、参考时刻的轨道面倾角、升交点赤经。
在一种可选的实现方式中,所述第二***消息中还包括所述第二卫星的标识、星历参考时刻以及所述第二卫星在所述星历参考时刻的平近点角。
第四方面,本申请实施例提供一种卫星通信装置,该装置包括:
处理模块和发送模块;
所述处理模块用于通过所述发送模块向终端设备发送第一***消息,以使所述终端设备根据所述第一***消息确定所述第一卫星所属卫星网络的拓扑,其中,所述第一***消息用于指示所述第一卫星在星历参考时刻的平近点角。
在一种可选的实现方式中,所述第一***消息中包括所述第一卫星的标识、星历参考时刻以及所述第一卫星在所述星历参考时刻的平近点角。
在一种可选的实现方式中,所述第一***消息中还包括当前上线的卫星的标识和/或当前离线的卫星的标识。
在一种可选的实现方式中,所述装置还包括:
接收模块,用于接收所述终端设备发送的第一请求消息,所述第一请求消息用于请求所述第一卫星发送所述第一***消息;
所述发送模块,具体用于根据所述第一请求消息,向所述终端设备发送所述第一***消息。
在一种可选的实现方式中,所述装置还包括:
接收模块,用于接收所述终端设备发送的第二请求消息,所述第二请求消息用于请求获取第二卫星的星历参数;
所述发送模块,还用于根据所述第二请求消息,向所述终端设备发送第二***消息,所述第二***消息用于指示所述第二卫星的星历参数。
在一种可选的实现方式中,所述第二***消息中包括所述卫星网络的轨道半长轴平方根、偏心率、近地点角距、参考时刻的轨道面倾角、升交点赤经。
在一种可选的实现方式中,所述第二***消息中还包括所述第二卫星的标识、星历参考时刻以及所述第二卫星在所述星历参考时刻的平近点角。
第五方面,本申请实施例提供一种终端设备,所述终端设备包括:存储器、处理器和收发器;所述处理器用于与所述存储器耦合,读取并执行所述存储器中的指令,以实现上述第一方面所述的方法步骤;所述收发器与所述处理器耦合,由所述处理器控制所述收发器进行消息收发。
第六方面,本申请实施例提供一种卫星,包括:存储器、处理器和收发器;所述处理器用于与所述存储器耦合,读取并执行所述存储器中的指令,以实现上述第二方面所述的方法步骤;所述收发器与所述处理器耦合,由所述处理器控制所述收发器进行消息收发。
第七方面,本申请实施例提供一种计算机程序产品,所述计算机程序产品包括计算机程序代码,当所述计算机程序代码被计算机执行时,使得所述计算机执行上述第一方面或上述第二方面所述的方法。
第八方面,本申请实施例提供一种计算机可读存储介质,所述计算机存储介质存储有计算机指令,当所述计算机指令被计算机执行时,使得所述计算机执行上述第一方面或上述第二方面所述的方法的指令。
第九方面,本申请实施例提供一种芯片,所述芯片与存储器相连,用于读取并执行所述存储器中存储的软件程序,以实现上述第一方面或上述第二方面所提供的方法。
第十方面,本申请实施例提供一种装置,包括:输入接口电路,逻辑电路,输出接口电路,其中,所述逻辑电路用于执行上述第一方面所述的方法,或者,上述第二方面所述的方法。
图1为导航电文的结构示意图;
图2为GPS的应用场景示意图;
图3为本申请实施例提供的通信方法的示例性***架构示意图;
图4为卫星轨道参数的示意图;
图5为卫星轨道参数的示意图;
图6为本申请实施例提供的通信方法实施例一的交互流程图;
图7为本申请实施例提供的通信方法实施例二的交互流程图;
图8为本申请实施例提供的通信方法实施例三的交互流程图;
图9为本申请实施例提供的一种卫星通信装置的模块结构图;
图10为本申请实施例提供的另一种卫星通信装置的模块结构图;
图11为本申请实施例提供的再一种卫星通信装置的模块结构图;
图12为本申请实施例提供的一种终端设备的结构示意图;
图13为本申请实施例提供的一种卫星的结构示意图。
传统的GPS使用导航电文作为定位和导航的数据基础。导航电文包括了卫星的星历、卫星工作状态、时间***、卫星钟运行状态、轨道摄动参数、大气折射改动和由C/A码捕获码等导航信息的数据码。导航电文由主帧、子帧、字码和页面组成。图1为导航电文的结构示意图,如图1所示,导航电文的基本单位为一个1500比特的主帧。一个主帧包括5个子帧,其中第1个子帧、第2个子帧、第3个子帧中的每个子帧分别包括10个字码,每个字码包括30比特,每个比特的传输时间为0.02秒。该3个子帧用于播发卫星的星历以及时钟修正参数。第4个子帧和第5个子帧分别包括25个页面,每个页面包括750比特,每个比特的传输时间为0.02秒。该2子帧用于播发所有25颗卫星的历书。导航电文的传输速率为50比特/秒,一个主帧为1500比特,因此,导航电文的一个主帧的传输时间为30秒。1个主帧的1500比被分配给5个子帧,每个子帧300比特。因此,第1个子帧、第2个子帧和第3个子帧可以每30秒重复一次,并且每小时更新一次。一个主帧可以传输第4个子帧和第5个子帧中各一个页面,因此,第4个子帧和第5个子帧需要25个主帧来传输。因此,一个完整的导航电文需要25个主帧来传输,每个主帧传输时间为30秒,因此,传输一个完整的导航电文需要耗时750秒。对于终端设备来说,为了获得完整的导航电文,就需要持续监听导航电文750秒以上。在上述过程中,一方面,终端设备需要持续监听导航电文较长时间,因此开销较大。另一方面,终端设备为了获取到每颗卫星的历史,需要耗时750秒,这样也会产生较大的时延。
上述的传统GPS,其主要的应用场景是精确定位和导航。图2为GPS的应用场景示意图,如图2所示,由工作人员编制导航电文,并将导航电文输入地面主控站,由地面主控站将导航电文传输到地面注入站,由地面注入站将导航电文注入到卫星的存储***。卫星再按照上述的方式,向终端设备播发导航电文。终端设备解译导航电文,计算出当前的位置、速度等信息。在上述场景中,需要进行精确的定位以及卫星预报,因此,终端设备需要通过导航电文获知卫星的星历以及所有卫星的历书。其中,卫星的星历包括时间参数、开普勒轨道参数和轨道摄动参数,基于这些参数,可以得到当前观测到的卫星的精确位置,进而实现终端设备的定位。所有卫星的历书包括了所有卫星的基本轨道参数,基于这些参数,可以进行卫星预报。
卫星除了可以应用在上述GPS***之外,随着移动通信技术的不断发展,还可以将卫星应用于移动通信中。这种基于卫星的移动通信可以称为卫星通信。卫星通信与其他移动通信方式一样,需要实现语音通话、视频通话、观看视频等各项业务,因此,卫星通信***需要保持较低的时延以及较小的开销,以保证上述各项业务的正常运行。而上述的GPS***中通过导航电文播发卫星的星历和历书方法由于会产生较大的开销和时延,并不能适用于卫星通信***中。
另一方面,在卫星通信***中,终端设备获取卫星的星历和历书,主要用于确定当前观测到的卫星的位置信息,根据该位置信息确定卫星网络的拓扑,并进行卫星过顶预测,进而进行业务数据的交互等。而确定卫星网络的拓扑时对卫星的位置信息的精度要求较低,在位 置信息的精度较低时仍然可以确定出卫星网络的拓扑。因此,对于卫星通信***来说,仅需要获取必要的星历参数,基于这些参数确定出当前观测到的卫星的位置信息,所得到的位置信息可以使得终端设备确定出卫星网络的拓扑。另外,对于一些轨道平面分布均匀并且轨道平面中的卫星分布均匀的卫星网络来说,卫星之间的位置关系相对固定。因此,在获知当前观测到的卫星的位置信息的基础上,可以根据卫星之间的位置关系,得到卫星网络中其他卫星的位置信息,进而得到卫星网络的拓扑。
基于上述的分析,本申请实施例提供一种应用于卫星通信***的通信方法,终端设备仅获取必要的星历参数,根据该必要的星历参数,确定当前观测到的卫星的位置信息以及卫星网络中其他卫星的位置信息。根据当前观测到的卫星的位置信息以及其他卫星的位置信息,可以确定出卫星网络的拓扑,进而可以进行卫星过顶预测等。
图3为本申请实施例提供的通信方法的示例性***架构示意图,值得说明的是,图3是以卫星网络与5G网络融合为例进行说明,但这并不能作为对本申请实施例的限制,本申请实施例所提供的通信方法还可以应用于卫星网络与2G网络、3G网络、4G网络等融合的***中。如图3所示,卫星网络与5G网络融合的***中包括:终端设备、部署在卫星上的5G基站、地面站以及5G核心网。在该***中,5G基站部署在卫星网络的卫星上,并通过无线链路与地面的5G核心网通信,以进行信令交互、业务数据传输等。各卫星之间存在无线链路,通过这些链路可以实现5G基站之间的信令交互和用户数据传输。
终端设备也可以称为终端Terminal、用户设备(user equipment,UE)、移动台(mobile station,MS)、移动终端(mobile terminal,MT)等。该终端设备可以是手机(mobile phone)、平板电脑(pad)、带无线收发功能的电脑、虚拟现实(virtual reality,VR)终端设备、增强现实(augmented reality,AR)终端设备、工业控制(industrial control)中的无线终端、无人驾驶(self driving)中的无线终端、远程手术(remote medical surgery)中的无线终端、智能电网(smart grid)中的无线终端、运输安全(transportation safety)中的无线终端、智慧城市(smart city)中的无线终端、智慧家庭(smart home)中的无线终端等。
终端设备通过5G新空口与部署在卫星上的5G基站通信。
5G基站主要用于提供无线接入服务,调度无线资源以供接入的终端设备使用,同时,5G基站还提供可靠的无线传输协议和数据加密协议等。
值得说明的是,在卫星网络与2G网络、3G网络、4G网络等融合的***中,部署在卫星中的还可以是全球移动通信***(global system for mobile communication,GSM)或码分多址(code division multiple access,CDMA)中的基站(base transceiver station,BTS),也可以是宽带码分多址(wideband code division multiple access,WCDMA)中的基站(NodeB),还可以是LTE中的演进型基站(eNB或e-NodeB,evolutional Node B)等。
5G基站与5G基站之间可以通过Xn接口建立无线链路。
5G核心网用于进行用户接入控制、移动性管理、会话管理、用户安全认证、计费等业务。5G核心网由多个功能单元组成,这些功能单元可以划分为控制面的功能实体和用户面的功能实体。控制面功能实体主要包括接入与移动管理功能(access and mobility management function,AMF)和会话管理功能(session management function,SMF)。用户面功能实体主要包括用户面功能(user plane function,UPF)。其中,AMF负责用户接入、安全认证和移动性管理,SMF提供服务连续性、服务的不间断用户体验。UPF负责管理用户面数据的传输、流量统计、安全窃听等。
值得说明的是,在卫星网络与2G网络、3G网络、4G网络等融合的***中,上述的5G 核心网可以替换为2G网络的核心网、3G网络的核心网、4G网络的核心网。
5G核心网与5G基站之间可以通过NG接口建立无线链路。
本申请以下实施例主要涉及上述的终端设备以及部署了5G基站的卫星之间的交互过程。
在说明终端设备与卫星的交互过程之前,首先对前文所描述的必要的星历参数进行说明。
如前文所描述的,在GPS中,卫星的星历包括时间参数、开普勒轨道参数和轨道摄动参数,基于这些参数,可以得到当前观测到的卫星的精确位置。其中,时间参数包括星历参考时刻t
0e,开普勒轨道参数包括:轨道半长轴平方根
偏心率e、近地点角距ω、参考时刻的轨道面倾角i
0、升交点赤经Ω
0、参考时刻平近点角M
0,轨道摄动参数包括:平近地点角修正值、升交点赤经变化率、轨道平面倾角变化率、纬度幅角的正余弦调和改正项振幅、轨道正面倾角的正余弦调和改正项振幅、轨道半径的正余弦调和改正项振幅。
在本申请实施例中,基于上述时间参数中的星历参考时刻t
0e,以及开普勒轨道参数中的轨道半长轴平方根
偏心率e、近地点角距ω、参考时刻的轨道面倾角i
0,升交点赤经Ω
0,参考时刻平近点角M
0,可以得到当前观测到的卫星的位置信息以及卫星网络中其他卫星的位置信息,因此,在本申请实施例中,将这些参数称为必要的星历参数。终端设备获取到这些必要的星历参数之后,可以确定出当前观测到的卫星的位置信息以及卫星网络中其他卫星的位置信息。
图4为卫星轨道参数的示意图,图5为卫星轨道参数的示意图,参照图4和图5,在卫星网络中,轨道半长轴a、轨道偏心率由为卫星网络决定,因此,轨道半长轴平方根
和偏心率e不会发生改变。近地点角距,是指在轨道平面上,升交点与近地点之间的地心夹角,因此,近地点角距ω不会发生改变。另外,参考时刻的轨道面倾角i
0和升交点赤经Ω
0也由卫星网络决定。而参考时刻平近点角M
0为时间的函数,该参数决定了卫星在轨道上的瞬时位置,因此,该参数会随参考时间变化而变化。
如上述图4和图5所示,对于一些轨道平面分布均匀并且轨道平面中的卫星分布均匀的卫星网络来说,卫星之间的位置关系相对固定。这样的卫星网络例如可以是Walker星座等。以Walker星座为例,其具有圆轨道、轨道面倾角相同、轨道面升交点均匀间隔、轨道内卫星均匀间隔、相邻轨道面之间卫星等相位间隔的特点。因此,对于如Walker星座等卫星之间位置相对固定的卫星网络来说,上述必要的星历参数中的轨道半长轴平方根
偏心率e、近地点角距ω、参考时刻的轨道面倾角i
0,升交点赤经Ω
0这些参数由卫星网络决定,对于卫星网络中的卫星来说,这些参数不会发生变化。因此,在本申请实施例中,一方面,终端设备可以通过特定的方式获取到这些参数,并将这些参数存储在终端设备中,当终端设备每次需要确定卫星的位置信息时,可以直接使用这些参数,而无需卫星每次发送。另一方面,上述必要的星历参数中的星历参考时刻t
0e和参考时刻平近点角M
0,在卫星运行过程中会发生变化,因此可以由卫星发送给终端设备,终端设备根据当前观测到的卫星发送的星历参考时刻t
0e和参考时刻平近点角M
0,以及上述由卫星网络决定的不会发生变化的参数,可以确定出当前观测到的卫星以及卫星网络中其卫星的位置信息,进而得到卫星网络的拓扑。
其中,终端设备可以基于前述的星历参考时刻t
0e以及开普勒轨道参数中的轨道半长轴平方根
偏心率e、近地点角距ω、参考时刻的轨道面倾角i
0,升交点赤经Ω
0,参考时刻平近点角M
0,使用如下公式(1)至公式(12)推导得出当前观测到的卫星的位置信息,该位置信息为位置坐标(X
k,Y
k,Z
k)。
1、通过公式(1)计算半长轴
2、通过公式(2)计算卫星平均角速度n
0
3、通过公式(3)计算观测时刻t到星历参考时刻t
0e的时间差t
k
t
k=t-t
0e (3)
4、通过公式(4)计算平近点角M
k
M
k=M
0+n
0t
k (4)
5、通过公式(5)迭代计算偏近点角E
k
E
k=M
k+e sin E
k (5)
6、通过公式(6)计算真近点角f
k
7、通过公式(7)计算纬度幅角参数φ
k
φ
k=f
k+ω (7)
8、通过公式(8)计算向径r
k
r
k=a(1-e cos E
k) (8)
9、通过公式(9)计算卫星在轨道平面内的坐标(x
k,y
k)
10、通过公式(10)改正升交点的经度Ω
k
11、通过公式(11)计算轨道倾角i
i=i
0+δi (11)
12、通过公式(12)当前观测到的卫星的位置信息,该位置信息为位置坐标(X
k,Y
k,Z
k)
对于上述的Walker星座等具有圆轨道、轨道面倾角相同、轨道面升交点均匀间隔、轨道内卫星均匀间隔、相邻轨道面之间卫星等相位间隔的特点的卫星网络,由于卫星网络中每颗卫星在同一轨道面内为等间隔分布,因此,在计算出当前观测出的卫星的位置信息的基础上,根据轨道面分布各卫星之间的位置间隔,可以计算出同一轨道面内其他卫星的位置信息。同时,这些卫星网络的不同轨道面之间也为等间隔分布,因此,在计算出一个轨道面内卫星的位置信息的基础上,根据各轨道面之间的位置间隔,可以计算出其他轨道面内的卫星的位置信息,从而得到卫星网络的拓扑。
对于上述由卫星网络决定的不会发生变化的星历参数,终端设备可以通过如下两种方式 中任意一种获取:
第一种方式中,在终端设备出厂时,将上述不会发生变化的星历参数存储至终端设备中。
第二种方式中,在终端设备首次入网时,由卫星将上述不会发生变化的星历参数发送给终端设备,由终端设备存储。
其中,终端设备首次入网可以是指终端设备通过随机接入过程接入网络,也可以是指终端设备从一个网络切换至另一个网络。
对于会发生改变的星历参数,包括星历参考时刻t
0e和参考时刻平近点角M
0,终端设备可以通过如下两种方式中的任意一种获取:
第一种方式中,卫星按照预设的周期向终端设备广播会发生改变的星历参数。
第二种方式中,终端设备需要使用星历参数确定卫星网络的拓扑时,向卫星请求发送会发生改变的星历参数。
以下通过终端设备与卫星的消息交互过程详细说明上述各种可选方式实施过程。
图6为本申请实施例提供的通信方法实施例一的交互流程图,如图6所示,终端设备与卫星交互过程包括:
S601、卫星向终端设备发送主***信息块(master information block,MIB)。
MIB中包括终端设备接入网络的基本信息,通过这些信息,终端设备可以获知剩余最小***信息(remaining minimum system information,RMSI)的接收方式。
S602、卫星向终端设备发送RMSI。
终端设备在获知RMSI的接收方式之后,按照该接收方式接收卫星发送的RMSI。
RMSI中携带了终端设备接入网络的必要信息,包括上行初始带宽部分(bandwidth part,BWP)、初始BWP中的信道配置、小区半静态配比等。
S603、卫星向终端设备发送第一***消息,该第一***消息用于指示当前观测到的卫星在星历参考时刻的平近点角。
本实施例以及下述图7所示流程中,与终端设备交互的卫星为终端设备当前观测到的卫星,该当前观测到的卫星可以称为第一卫星。
另外,本申请实施例中可以将“星历参考时刻”简称为“参考时刻”,例如,卫星在参考时刻的平近点角表示卫星在星历参考时刻的平近点角。
上述第一***消息中可以携带上述的必要的星历参数中的星历参考时刻t
0e和参考时刻平近点角M
0,同时,第一***消息中携带终端设备当前观测到的卫星的标识。
上述三个参数中,终端设备根据卫星的标识,可以获知当前观测到的是卫星网络中的哪颗卫星,终端设备根据星历参考时刻t
0e和参考时刻平近点角M
0可以获知在参考时间t
0e时卫星的平近点角M
0。
除了上述三个参数之外,其余的不会发生变化的必要的星历参数,均预先存储在终端设备中。终端设备预先存储其余的不会发生变化的星历参数的方式可以为前述的终端设备出厂时预先存储,或者为前述的终端设备首次入网时由卫星向终端设备进行发送。
***消息可以包括MIB和***消息块(system information blocks,SIB),在本申请实施例中,可以通过对SIB进行扩展,将扩展的SIB作为上述第一***消息,在该消息中携带星历参考时刻t
0e、参考时刻平近点角M
0以及卫星的标识,以指示当前观测到的卫星在参考时刻的平近点角。
作为一种示例,第一***消息中携带的星历参考时刻t
0e可以为16比特,取值范围可以为0度至360度,参考时刻平近点角M
0可以为32比特,单位为秒,卫星的标识可以为16比 特,取值范围可以为0至65535。
S604、终端设备根据第一***消息以及预先存储的不会发生改变的星历参数,确定卫星网络的拓扑。
卫星可以按照预设的周期广播上述第一***消息。
具体的确定方法可以参照前述的使用公式(1)确定卫星的位置信息进而确定卫星网络的拓扑中的描述,此处不再赘述。
本实施例中,终端设备接收卫星按照预设周期发送的第一***消息,该***消息用于指示当前观测到的卫星在参考时刻的平近点角,基于第一***消息以及终端设备预先存储的不会发生改变的星历参数,终端设备可以确定出当前观测到的卫星以及卫星网络中其他卫星的位置信息,进而可以得到卫星网络的拓扑。由于第一***消息仅用于指示当前观测到的卫星在参考时刻的平近点角,即第一***信息只需要携带较少的参数,因此,终端设备仅需要较少的时延和较小的开销,即可确定出卫星网络的拓扑,因而可以满足卫星通信***时延低、开销小的要求。
在上述实施例一中,卫星按照预设的周期,主动地周期性地广播第一***消息。作为另一种方式,卫星在接收到终端设备的请求消息后,向终端设备发送上述第一***消息。
图7为本申请实施例提供的通信方法实施例二的交互流程图,如图7所示,终端设备与卫星交互过程包括:
S701、卫星向终端设备发送MIB。
该步骤的执行过程与前述的步骤S601相同,可以参照前述步骤S601,此处不再赘述。
S702、卫星向终端设备发送RMSI。
该步骤的执行过程与前述的步骤S602相同,可以参照前述步骤S602,此处不再赘述。
S703、终端设备向卫星发送第一请求消息。
该第一请求消息用于请求卫星发送指示当前观测到的卫星在参考时刻的平近点角的第一***消息。
可选的,该第一请求消息可以为***消息,例如SIB消息。
作为一种可选的实施方式,可以在终端设备中设置一个定时器,通过该定时器控制上述第一请求消息的发送。
该定时器的初始值可以在终端设备在网络中注册成功时,由网络设备向终端设备指示。示例性的,终端设备向核心网发起注册请求,核心网在向终端设备返回注册成功的Registration Accept消息时,在Registration Accept消息中携带上述定时器的初始值。
当终端设备注册在网络中时,定时器按照如下方式控制上述第一请求消息的发送:
当终端设备接收到第一***消息后,定时器重置初始值,并开始计时。
当定时器过期后,触发终端设备向卫星发送上述第一请求消息,以请求卫星发送第一***消息,同时,终端设备终止定时器。
当终端设备从网络中注销时,定时器终止。
S704、卫星向终端设备发送第一***消息,该第一***消息用于指示当前观测到的卫星在参考时刻的平近点角。
该步骤的执行过程与前述的步骤S603相同,可以参照前述步骤S603,此处不再赘述。
S705、终端设备根据第一***消息以及预先存储的不会发生改变的星历参数,确定卫星网络的拓扑。
该步骤的执行过程与前述的步骤S604相同,可以参照前述步骤S604,此处不再赘述。
本实施例中,终端设备主动向卫星发送第一请求消息,卫星根据该第一请求消息,向终端设备发送第一***消息,该第一***消息用于指示当前观测到的卫星在参考时刻的平近点角,基于第一***消息以及终端设备预先存储的不会发生改变的星历参数,终端设备可以确定出当前观测到的卫星以及卫星网络中其他卫星的位置信息,进而可以得到卫星网络的拓扑。由于第一***消息仅用于指示当前观测到的卫星在参考时刻的平近点角,即第一***信息只需要携带较少的参数,因此,终端仅需要较少的时延和较小的开销,即可确定出卫星网络的拓扑,因而可以满足卫星通信***时延低、开销小的要求。
在上述实施例一和实施例二中,第一***消息用于指示当前观测到的卫星在参考时刻的平近点角,具体的,第一***消息中可以携带星历参考时刻t
0e、参考时刻平近点角M
0、当前观测到的卫星的标识。在此基础上,作为一种可选的实施方式,第一***消息中还可以携带当前最新上线的卫星的标识和/或当前最新离线的卫星的标识。
终端设备注册到网络之后,可以在终端设备上存储一个卫星列表,该卫星列表中的卫星为当前处于上线状态的卫星。终端设备可以根据该卫星列表,选择合适的卫星进行通信,以发起业务请求、获取用户数据等。当卫星网络中的某些卫星的运行状态发生变化,例如某个卫星刚加入卫星网络、某个卫星从离线状态变为上线状态、某个卫星由于故障或节能等原因从上线状态变为离线状态,在这种情况下,如果不对终端设备上存储的卫星列表同步进行更新,则可能造成终端设备无法正常发送消息等后果。因此,在本申请实施例中,可以利用上述第一***消息,在该第一***消息中携带星历参考时刻t
0e、参考时刻平近点角M
0、当前观测到的卫星的标识的同时,还可以携带最新上线的卫星的标识和/或最新离线的卫星的标识。终端设备在接收到第一***消息后,可以根据其所携带的最新上线的卫星的标识和/或最新离线的卫星的标识,更新本地存储的卫星列表,从而使得本地存储的卫星列表中的卫星的运行状态与实际的运行状态一致,进而保证终端设备可以与卫星进行正常通信。
在上述各实施例中,终端设备从卫星接收第一***消息,该第一***消息中携带星历参考时刻t
0e、参考时刻平近点角M
0、当前观测到的卫星的标识,即该第一***消息中仅携带会发生改变的必要的星历参数,其余不会发生改变的星历参数由终端设备预先存储在本地。如前文所描述的,可以在出厂时将不会发生改变的星历参数存储在终端设备中,或者,也可以在终端设备首次入网时将不会发生改变的星历参数存储在终端设备中。以下说明在终端设备首次入网时将不会发生改变的星历参数存储在终端设备中的过程。
图8为本申请实施例提供的通信方法实施例三的交互流程图,下述流程中与终端设备交互的卫星称为第二卫星,该第二卫星为在首次入网时终端设备观测到的卫星,该第二卫星与前述的第一卫星可以为同一卫星,也可以为不同卫星。如图8所示,终端设备与卫星交互过程包括:
S801、卫星向终端设备发送MIB。
MIB中包括终端设备接入网络的基本信息,通过这些信息,终端设备可以获知RMSI的接收方式。
S802、卫星向终端设备发送RMSI。
终端设备在获知RMSI的接收方式之后,按照该接收方式接收卫星发送的RMSI。
RMSI中携带了终端设备接入网络的必要信息,包括上行初始BWP、初始BWP中的信道配置、小区半静态配比等。
S803、终端设备向卫星发送第二请求消息。
该第二请求消息用于请求卫星发送指示卫星的星历参数的第二***消息。
可选的,该第一请求消息可以为***消息,例如SIB消息。
示例性的,终端设备首次入网时,判断终端设备上是否保存了卫星的星历参数,如果未保存则,则终端设备在接收到卫星发送的RMSI之后,通过本步骤向卫星发送第二请求消息,以请求卫星发送第二***消息。
S804、卫星向终端设备发送第二***消息。
该第二***消息用于指示卫星的星历参数。
首先,该第二***消息中可以携带不会发生改变的轨道半长轴平方根
偏心率e、近地点角距ω、参考时刻的轨道面倾角i
0,升交点赤经Ω
0。终端设备从第二***消息中读取到这些参数之后,将这些参数存储至终端设备中,在终端设备入网之后至从网络退出之前的过程中,终端设备可以直接使用这些参数。
其次,该第二***消息中还可以携带星历参考时刻t
0e、参考时刻平近点角M
0、当前观测到的卫星的标识。其中,当前观测到的卫星的标识为第二卫星的标识,星历参考时刻t
0e和参考时刻平近点角M
0与前述的第一***消息中的含义相同,此处不再赘述。基于这些参数,终端设备可以在入网时即可确定出卫星网络的拓扑。在此基础上,终端设备可以基于前述的实施例,持续获取不断变化的星历参考时刻t
0e、参考时刻平近点角M
0,并不断得到卫星网络的更新后的拓扑。
再次,可选的,上述第二***消息中还可以携带卫星网络的特有的网络参数。
以卫星网络为Walker星座为例,上述第二***消息中还可以携带Walker星座的如下特有参数:
每个轨道面上的卫星数、星座轨道面的数量、相邻轨道面的相位差。
终端设备获取并保存这些特有的网络参数后,在根据上述的不会发生改变的轨道半长轴平方根
偏心率e、近地点角距ω、参考时刻的轨道面倾角i
0,升交点赤经Ω
0,以及会发生改变的星历参考时刻t
0e、参考时刻平近点角M
0、当前观测到的卫星的标识,使用前文所描述的方法计算得到当前观测到的卫星的位置信息后,根据上述特有参数中的每个轨道面上的卫星数,可以确定卫星网络中一个轨道面内各卫星的位置间隔,进而根据各卫星的位置间隔,可以计算出同一轨道面内其他卫星的位置信息。进而,根据上述特有参数中的星座轨道面的数量、相邻轨道面的相位差,可以确定卫星网络各轨道面之间的位置间隔,进而,根据各轨道面之间的位置间隔,可以计算出其他轨道面内的卫星的位置信息,从而得到卫星网络的拓扑
另外,可选的,上述第二***消息中还可以携带当前处于上线状态的卫星的标识。
终端设备根据当前处于上线状态的卫星的标识,可以生成前文所描述的卫星列表。终端设备在后续运行过程中,可以从卫星列表中选择合适的卫星进行通信,以发起业务请求、获取用户数据等。
可续的,上述第二***消息可以为SIB。
S805、终端设备根据第二***消息确定卫星网络的拓扑。
具体的确定方法可以参照前述的使用公式(1)确定卫星的位置信息进而确定卫星网络的拓扑中的描述,此处不再赘述。
本实施例中,终端设备在首次入网时向卫星发送第二请求消息,卫星根据该第二请求消息,向终端设备发送第二***消息,该第二***消息中携带卫星的必要的星历参数,终端设备根据必要的星历参数,可以确定出当前观测到的卫星以及卫星网络中其他卫星的位置信息,进而可以得到卫星网络的拓扑。终端设备在首次入网时通过第二***消息获取并保存不会发 生改变的必要的星历参数,在退出网络之前,终端设备可以直接使用这些参数,无需再从卫星上获取,从而可以降低时延和开销,满足卫星通信***时延低、开销小的要求。
图9为本申请实施例提供的一种卫星通信装置的模块结构图,该装置可以为前述实施例所描述的终端设备,也可以为能够支持终端设备实现本申请实施例提供的方法中的终端设备的功能的装置,例如该装置可以是终端设备中的装置或芯片***。如图9所示,该装置包括:
接收模块901,用于接收第一卫星发送的第一***消息,该第一***消息用于指示该第一卫星在星历参考时刻的平近点角。
处理模块902,用于根据上述第一***消息,确定上述第一卫星所属卫星网络的拓扑。
在一种可能的实施方式中,上述第一***消息中包括上述第一卫星的标识、星历参考时刻以及上述第一卫星在上述星历参考时刻的平近点角。
在一种可能的实施方式中,上述第一***消息中还包括当前上线的卫星的标识和/或当前离线的卫星的标识。
继续参照图9,在一种可能的实施方式中,上述装置还包括:
发送模块903,用于向上述第一卫星发送第一请求消息,该第一请求消息用于请求上述第一卫星发送上述第一***消息。
在一种可能的实施方式中,发送模块903,用于向第二卫星发送第二请求消息,该第二请求消息用于请求获取上述第二卫星的星历参数。接收模块901,还用于接收第二卫星发送的第二***消息,该第二***消息用于指示上述第二卫星的星历参数。
在一种可能的实施方式中,上述第二***消息中包括上述卫星网络的轨道半长轴平方根、偏心率、近地点角距、参考时刻的轨道面倾角、升交点赤经。
在一种可能的实施方式中,上述第二***消息中还包括上述第二卫星的标识、星历参考时刻以及上述第二卫星在上述星历参考时刻的平近点角。
图10为本申请实施例提供的另一种卫星通信装置的模块结构图,该装置可以为前述实施例所描述的卫星,也可以为能够支持卫星实现本申请实施例提供的方法中的卫星的功能的装置,例如该装置可以是卫星中的装置或芯片***。如图10所示,该装置包括:
处理模块1001和发送模块1002。
处理模块1001用于通过发送模块1002向终端设备发送第一***消息,以使终端设备根据上述第一***消息确定上述第一卫星所属卫星网络的拓扑,其中,上述第一***消息用于指示上述第一卫星在星历参考时刻的平近点角。
在一种可能的实施方式中,上述第一***消息中包括上述第一卫星的标识、星历参考时刻以及上述第一卫星在上述星历参考时刻的平近点角。
在一种可能的实施方式中,上述第一***消息中还包括当前上线的卫星的标识和/或当前离线的卫星的标识。
继续参照图9,在一种可能的实施方式中,上述装置还包括:
接收模块1003,用于接收上述终端设备发送的第一请求消息,该第一请求消息用于请求上述第一卫星发送上述第一***消息。发送模块1002,具体用于根据上述第一请求消息,向终端设备发送上述第一***消息。
在一种可能的实施方式中,接收模块1003,用于接收上述终端设备发送的第二请求消息,该第二请求消息用于请求获取第二卫星的星历参数。发送模块1002,还用于根据上述第二请求消息,向上述终端设备发送第二***消息,该第二***消息用于指示上述第二卫星的星历参数。
在一种可能的实施方式中,上述第二***消息中包括上述卫星网络的轨道半长轴平方根、偏心率、近地点角距、参考时刻的轨道面倾角、升交点赤经。
在一种可能的实施方式中,上述第二***消息中还包括上述第二卫星的标识、星历参考时刻以及上述第二卫星在上述星历参考时刻的平近点角。
本申请实施例提供的卫星通信装置,可以执行上述方法实施例中的方法步骤,其实现原理和技术效果类似,在此不再赘述。
需要说明的是,应理解以上装置的各个模块的划分仅仅是一种逻辑功能的划分,实际实现时可以全部或部分集成到一个物理实体上,也可以物理上分开。且这些模块可以全部以软件通过处理元件调用的形式实现;也可以全部以硬件的形式实现;还可以部分模块通过处理元件调用软件的形式实现,部分模块通过硬件的形式实现。例如,确定模块可以为单独设立的处理元件,也可以集成在上述装置的某一个芯片中实现,此外,也可以以程序代码的形式存储于上述装置的存储器中,由上述装置的某一个处理元件调用并执行以上确定模块的功能。其它模块的实现与之类似。此外这些模块全部或部分可以集成在一起,也可以独立实现。这里所描述的处理元件可以是一种集成电路,具有信号的处理能力。在实现过程中,上述方法的各步骤或以上各个模块可以通过处理器元件中的硬件的集成逻辑电路或者软件形式的指令完成。
例如,以上这些模块可以是被配置成实施以上方法的一个或多个集成电路,例如:一个或多个特定集成电路(application specific integrated circuit,ASIC),或,一个或多个微处理器(digital signal processor,DSP),或,一个或者多个现场可编程门阵列(field programmable gate array,FPGA)等。再如,当以上某个模块通过处理元件调度程序代码的形式实现时,该处理元件可以是通用处理器,例如中央处理器(central processing unit,CPU)或其它可以调用程序代码的处理器。再如,这些模块可以集成在一起,以片上***(system-on-a-chip,SOC)的形式实现。
在上述实施例中,可以全部或部分地通过软件、硬件、固件或者其任意组合来实现。当使用软件实现时,可以全部或部分地以计算机程序产品的形式实现。该计算机程序产品包括一个或多个计算机指令。在计算机上加载和执行该计算机程序指令时,全部或部分地产生按照本申请实施例所描述的流程或功能。上述计算机可以是通用计算机、专用计算机、计算机网络、或者其他可编程装置。上述计算机指令可以存储在计算机可读存储介质中,或者从一个计算机可读存储介质向另一个计算机可读存储介质传输,例如,上述计算机指令可以从一个网站站点、计算机、服务器或数据中心通过有线(例如同轴电缆、光纤、数字用户线(DSL))或无线(例如红外、无线、微波等)方式向另一个网站站点、计算机、服务器或数据中心进行传输。上述计算机可读存储介质可以是计算机能够存取的任何可用介质或者是包含一个或多个可用介质集成的服务器、数据中心等数据存储设备。上述可用介质可以是磁性介质,(例如,软盘、硬盘、磁带)、光介质(例如,DVD)、或者半导体介质(例如固态硬盘solid state disk(SSD))等。
基于与本申请上述实施例提供的卫星通信方法的同一发明构思,本申请实施例还提供了一种卫星通信装置,用于实现上述实施例中的卫星通信方法,上述实施例的卫星通信方法中的部分或全部可以通过硬件来实现也可以通过软件来实现,当通过硬件实现时,参见图11所示,该卫星通信装置1100包括:
输入接口电路1102,逻辑电路1104,输出接口电路1106,还包括收发器1108和天线1110,收发器1108通过天线1110进行数据的收发。
其中,逻辑电路1104,用于执行图6-图8所示的卫星通信方法中终端设备或者卫星的方法步骤,具体请见前面方法实施例中的描述,此处不再赘述。在具体实现时,上述卫星通信装置1100可以是芯片或者集成电路。
图12为本申请实施例提供的一种终端设备的结构示意图。如图12所示,该终端设备1200可以包括:处理器121(例如CPU)、存储器122、收发器123;收发器123耦合至处理器121,处理器121控制收发器123的收发动作。存储器122中可以存储各种指令,以用于完成各种处理功能以及实现本申请实施例中终端设备执行的方法步骤。可选的,本申请实施例涉及的终端设备还可以包括:电源124、***总线125以及通信端口126。收发器123可以集成在终端设备的收发信机中,也可以为终端设备上独立的收发天线。***总线125用于实现元件之间的通信连接。上述通信端口126用于实现终端设备与其他外设之间进行连接通信。
在本申请实施例中,上述处理器121用于与存储器122耦合,读取并执行存储器122中的指令,以实现上述方法实施例中终端设备执行的方法步骤。收发器123与处理器121耦合,由处理器121控制收发器123进行消息收发,其实现原理和技术效果类似,在此不再赘述。
该图12中提到的***总线可以是外设部件互连标准(peripheral component interconnect,PCI)总线或扩展工业标准结构(extended industry standard architecture,EISA)总线等。该***总线可以分为地址总线、数据总线、控制总线等。为便于表示,图中仅用一条粗线表示,但并不表示仅有一根总线或一种类型的总线。通信接口用于实现数据库访问装置与其他设备(例如客户端、读写库和只读库)之间的通信。存储器可能包含随机存取存储器(random access memory,RAM),也可能还包括非易失性存储器(non-volatile memory),例如至少一个磁盘存储器。
上述的处理器可以是通用处理器,包括中央处理器CPU、网络处理器(network processor,NP)等;还可以是数字信号处理器DSP、专用集成电路ASIC、现场可编程门阵列FPGA或者其他可编程逻辑器件、分立门或者晶体管逻辑器件、分立硬件组件。
图13为本申请实施例提供的一种卫星的结构示意图。如图13所示,该卫星1300可以包括:处理器131(例如CPU)、存储器132、收发器133;收发器133耦合至处理器131,处理器131控制收发器133的收发动作。存储器132中可以存储各种指令,以用于完成各种处理功能以及实现本申请实施例中卫星执行的方法步骤。可选的,本申请实施例涉及的卫星还可以包括:电源134、***总线135以及通信端口136。收发器133可以集成在卫星的收发信机中,也可以为卫星上独立的收发天线。***总线135用于实现元件之间的通信连接。上述通信端口136用于实现卫星与其他外设之间进行连接通信。
在本申请实施例中,上述处理器131用于与存储器132耦合,读取并执行存储器132中的指令,以实现上述方法实施例中卫星执行的方法步骤。收发器133与处理器131耦合,由处理器131控制收发器123进行消息收发,其实现原理和技术效果类似,在此不再赘述。
该图12中提到的***总线可以是PCI总线或EISA总线等。上述***总线可以分为地址总线、数据总线、控制总线等。为便于表示,图中仅用一条粗线表示,但并不表示仅有一根总线或一种类型的总线。通信接口用于实现数据库访问装置与其他设备(例如客户端、读写库和只读库)之间的通信。存储器可能包含RAM,也可能还包括非易失性存储器(non-volatile memory),例如至少一个磁盘存储器。
上述的处理器可以是通用处理器,包括CPU、NP等;还可以是DSP、ASIC、FPGA或者其他可编程逻辑器件、分立门或者晶体管逻辑器件、分立硬件组件。
可选的,本申请实施例还提供一种计算机可读存储介质,该存储介质中存储有指令,当 其在计算机上运行时,使得计算机执行上述实施例中卫星的处理过程或终端设备的处理过程。
可选的,本申请实施例还提供一种运行指令的芯片,该芯片用于执行上述实施例中卫星的处理过程或终端设备的处理过程。
本申请实施例还提供一种程序产品,该程序产品包括计算机程序,该计算机程序存储在存储介质中,至少一个处理器可以从上述存储介质读取上述计算机程序,上述至少一个处理器执行上述实施例中卫星的处理过程或终端设备的处理过程。
在本申请实施例中,“至少一个”是指一个或者多个,“多个”是指两个或两个以上。“和/或”,描述关联对象的关联关系,表示可以存在三种关系,例如,A和/或B,可以表示:单独存在A,同时存在A和B,单独存在B的情况,其中A,B可以是单数或者复数。字符“/”一般表示前后关联对象是一种“或”的关系;在公式中,字符“/”,表示前后关联对象是一种“相除”的关系。“以下至少一项(个)”或其类似表达,是指的这些项中的任意组合,包括单项(个)或复数项(个)的任意组合。例如,a,b,或c中的至少一项(个),可以表示:a,b,c,a-b,a-c,b-c,或a-b-c,其中,a,b,c可以是单个,也可以是多个。
可以理解的是,在本申请的实施例中涉及的各种数字编号仅为描述方便进行的区分,并不用来限制本申请实施例的范围。
可以理解的是,在本申请的实施例中,上述各过程的序号的大小并不意味着执行顺序的先后,各过程的执行顺序应以其功能和内在逻辑确定,而不应对本申请的实施例的实施过程构成任何限定。
Claims (33)
- 一种卫星通信方法,其特征在于,包括:接收第一卫星发送的第一***消息,所述第一***消息用于指示所述第一卫星在星历参考时刻的平近点角;根据所述第一***消息,确定所述第一卫星所属卫星网络的拓扑。
- 根据权利要求1所述的方法,其特征在于,所述第一***消息中包括所述第一卫星的标识、星历参考时刻以及所述第一卫星在所述星历参考时刻的平近点角。
- 根据权利要求2所述的方法,其特征在于,所述第一***消息中还包括当前上线的卫星的标识和/或当前离线的卫星的标识。
- 根据权利要求1-3任一项所述的方法,其特征在于,所述接收第一卫星发送的第一***消息之前,还包括:向所述第一卫星发送第一请求消息,所述第一请求消息用于请求所述第一卫星发送所述第一***消息。
- 根据权利要求1-3任一项所述的方法,其特征在于,所述接收第一卫星发送的第一***消息之前,还包括:向第二卫星发送第二请求消息,所述第二请求消息用于请求获取所述第二卫星的星历参数;接收第二卫星发送的第二***消息,所述第二***消息用于指示所述第二卫星的星历参数。
- 根据权利要求5所述的方法,其特征在于,所述第二***消息中包括所述卫星网络的轨道半长轴平方根、偏心率、近地点角距、参考时刻的轨道面倾角、升交点赤经。
- 根据权利要求6所述的方法,其特征在于,所述第二***消息中还包括所述第二卫星的标识、星历参考时刻以及所述第二卫星在所述星历参考时刻的平近点角。
- 一种卫星通信方法,其特征在于,包括:向终端设备发送第一***消息,以使所述终端设备根据所述第一***消息确定第一卫星所属卫星网络的拓扑,其中,所述第一***消息用于指示所述第一卫星在星历参考时刻的平近点角。
- 根据权利要求8所述的方法,其特征在于,所述第一***消息中包括所述第一卫星的标识、星历参考时刻以及所述第一卫星在所述星历参考时刻的平近点角。
- 根据权利要求9所述的方法,其特征在于,所述第一***消息中还包括当前上线的卫星的标识和/或当前离线的卫星的标识。
- 根据权利要求8-10任一项所述的方法,其特征在于,所述向终端设备发送第一***消息之前,还包括:接收所述终端设备发送的第一请求消息,所述第一请求消息用于请求所述第一卫星发送所述第一***消息;所述向终端设备发送第一***消息,包括:根据所述第一请求消息,向所述终端设备发送所述第一***消息。
- 根据权利要求8-10任一项所述的方法,其特征在于,还包括:接收所述终端设备发送的第二请求消息,所述第二请求消息用于请求获取第二卫星的星历参数;根据所述第二请求消息,向所述终端设备发送第二***消息,所述第二***消息用于指 示所述第二卫星的星历参数。
- 根据权利要求12所述的方法,其特征在于,所述第二***消息中包括所述卫星网络的轨道半长轴平方根、偏心率、近地点角距、参考时刻的轨道面倾角、升交点赤经。
- 根据权利要求13所述的方法,其特征在于,所述第二***消息中还包括所述第二卫星的标识、星历参考时刻以及所述第二卫星在所述星历参考时刻的平近点角。
- 一种卫星通信装置,其特征在于,包括:接收模块,用于接收第一卫星发送的第一***消息,所述第一***消息用于指示所述第一卫星在星历参考时刻的平近点角;处理模块,用于根据所述第一***消息,确定所述第一卫星所属卫星网络的拓扑。
- 根据权利要求15所述的装置,其特征在于,所述第一***消息中包括所述第一卫星的标识、星历参考时刻以及所述第一卫星在所述星历参考时刻的平近点角。
- 根据权利要求16所述的装置,其特征在于,所述第一***消息中还包括当前上线的卫星的标识和/或当前离线的卫星的标识。
- 根据权利要求15-17任一项所述的装置,其特征在于,所述装置还包括:发送模块,用于向所述第一卫星发送第一请求消息,所述第一请求消息用于请求所述第一卫星发送所述第一***消息。
- 根据权利要求15-17任一项所述的装置,其特征在于,所述装置还包括:发送模块,用于向第二卫星发送第二请求消息,所述第二请求消息用于请求获取所述第二卫星的星历参数;所述接收模块,还用于接收第二卫星发送的第二***消息,所述第二***消息用于指示所述第二卫星的星历参数。
- 根据权利要求19所述的装置,其特征在于,所述第二***消息中包括所述卫星网络的轨道半长轴平方根、偏心率、近地点角距、参考时刻的轨道面倾角、升交点赤经。
- 根据权利要求20所述的装置,其特征在于,所述第二***消息中还包括所述第二卫星的标识、星历参考时刻以及所述第二卫星在所述星历参考时刻的平近点角。
- 一种卫星通信装置,其特征在于,包括:处理模块和发送模块;所述处理模块用于通过所述发送模块向终端设备发送第一***消息,以使所述终端设备根据所述第一***消息确定第一卫星所属卫星网络的拓扑,其中,所述第一***消息用于指示所述第一卫星在星历参考时刻的平近点角。
- 根据权利要求22所述的装置,其特征在于,所述第一***消息中包括所述第一卫星的标识、星历参考时刻以及所述第一卫星在所述星历参考时刻的平近点角。
- 根据权利要求23所述的装置,其特征在于,所述第一***消息中还包括当前上线的卫星的标识和/或当前离线的卫星的标识。
- 根据权利要求22-24任一项所述的装置,其特征在于,所述装置还包括:接收模块,用于接收所述终端设备发送的第一请求消息,所述第一请求消息用于请求所述第一卫星发送所述第一***消息;所述发送模块,具体用于根据所述第一请求消息,向所述终端设备发送所述第一***消息。
- 根据权利要求22-24任一项所述的装置,其特征在于,所述装置还包括:接收模块,用于接收所述终端设备发送的第二请求消息,所述第二请求消息用于请求获取第二卫星的星历参数;所述发送模块,还用于根据所述第二请求消息,向所述终端设备发送第二***消息,所述第二***消息用于指示所述第二卫星的星历参数。
- 根据权利要求26所述的装置,其特征在于,所述第二***消息中包括所述卫星网络的轨道半长轴平方根、偏心率、近地点角距、参考时刻的轨道面倾角、升交点赤经。
- 根据权利要求27所述的装置,其特征在于,所述第二***消息中还包括所述第二卫星的标识、星历参考时刻以及所述第二卫星在所述星历参考时刻的平近点角。
- 一种终端设备,其特征在于,包括:存储器、处理器和收发器;所述处理器用于与所述存储器耦合,读取并执行所述存储器中的指令,以实现权利要求1-7任一项所述的方法步骤;所述收发器与所述处理器耦合,由所述处理器控制所述收发器进行消息收发。
- 一种卫星,其特征在于,包括:存储器、处理器和收发器;所述处理器用于与所述存储器耦合,读取并执行所述存储器中的指令,以实现权利要求8-14任一项所述的方法步骤;所述收发器与所述处理器耦合,由所述处理器控制所述收发器进行消息收发。
- 一种计算机程序产品,其特征在于,所述计算机程序产品包括计算机程序代码,当所述计算机程序代码被计算机执行时,使得所述计算机执行权利要求1-7任一项或权利要求8-14任一项所述的方法。
- 一种计算机可读存储介质,其特征在于,所述计算机存储介质存储有计算机指令,当所述计算机指令被计算机执行时,使得所述计算机执行权利要求1-7任一项或权利要求8-14任一项所述的方法的指令。
- 一种装置,其特征在于,包括:输入接口电路,逻辑电路,输出接口电路,其中,所述逻辑电路用于执行如权利要求1~7中任一项所述的方法,或者,如权利要求8~14中任一项所述的方法。
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CN115412147A (zh) | 2022-11-29 |
CN112202484B (zh) | 2022-07-22 |
US11962396B2 (en) | 2024-04-16 |
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