CN112887008B - Space-based VDES (vertical double-layer data storage) based downlink communication link parameter determination system and method - Google Patents
Space-based VDES (vertical double-layer data storage) based downlink communication link parameter determination system and method Download PDFInfo
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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
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/02—Diversity systems; Multi-antenna system, i.e. transmission or reception using multiple antennas
- H04B7/04—Diversity systems; Multi-antenna system, i.e. transmission or reception using multiple antennas using two or more spaced independent antennas
- H04B7/0408—Diversity systems; Multi-antenna system, i.e. transmission or reception using multiple antennas using two or more spaced independent antennas using two or more beams, i.e. beam 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
- H04B7/1851—Systems using a satellite or space-based relay
- H04B7/18519—Operations control, administration or maintenance
Abstract
The invention discloses a system for determining parameters of a downlink communication link based on space-based VDES (vertical data storage systems), wherein the system parameters are set for acquiring satellite parameters and communication parameters, and a satellite-ground distance determination module is used for determining the satellite-ground distance under each nadir angle and the elevation angle of a ground shipway; the satellite-ground link loss determining module is used for calculating signal loss between satellite-ground links; the satellite transmitting terminal parameter determining module is used for calculating transmitting terminal parameters of a satellite; the slipway receiving end parameter determining module is used for determining receiving end parameters of the ground slipway; and the link analysis module is used for adjusting and optimizing the satellite transmitting end parameter determination module and the slipway receiving end parameter determination module. The invention is suitable for the design of load systems under the requirements of various satellite orbits and wave beams, and has better universality, better practicability, better systematicness, better scientificity and better expandability. The invention can control the transmitting power of the satellite downlink signal, thereby avoiding or reducing the interference to the ground system.
Description
Technical Field
The invention belongs to the field of satellite communication, and particularly relates to a system and a method for determining parameters of a downlink communication link based on space-based VDES (vertical double-diffusion evolution systems).
Background
Based on the original AIS, the VDES (VHF Data Exchange System, above-water VHF band Data Exchange System) expands new services such as LAIS (Long range AIS), ASM (Application Specific Messages) and VDE (VHF Data Exchange), and adopts different "exclusive lanes" for different information and opens up dedicated bands. Meanwhile, a satellite system is introduced into VDE communication to provide data exchange service under the condition that the coverage range of shore-based signals is out or no shore is provided. The introduction of the satellite in the VDES system enables an information service system facing offshore safety to become a mobile communication system with a world-wide feature, enables offshore safety guarantee and information interaction services to be expanded from near shore to far sea and even to the world, can realize real-time receiving, sending, processing and exchanging of marine ship information in the world, effectively improves ship communication capacity and offshore safety guarantee capacity, and has important functions and significance for supporting future realization of the internet of things on the sea and the like.
With the continuous deep research of the space-based VDES system (VDE-SAT) and the continuous promotion of engineering implementation, the coordination of the space-based VDES system and the ground VDES system, the construction cost and benefit of the space-based system, the optimal design of satellite load and the like become irretrievable key problems. The large-range coverage of the space-based system is an effective supplement to a ground network, but simultaneously brings the problems of interference and conflict between received signals, so that the signal power distribution and the cooperative working mode between the space-based system and the ground are required to be reasonably designed, the influence of the space-based system on the ground system is avoided, and particularly the interference on AIS signals with the highest priority cannot be caused.
In addition, since the VHF band allocated to the VDE-SAT has a narrow bandwidth (150 kHz bandwidth of 157.200-157.350 MHz and 150kHz bandwidth of 161.800-161.950 MHz), it is necessary to increase the communication capacity and cost-effectiveness ratio of the satellite system by using various multiple access methods. Therefore, in the prior art, the satellite system has the technical problems of small coverage area, low communication capacity, large interference to the ground, weak capability of solving AIS time slot conflict and the like.
Disclosure of Invention
The invention aims to provide a system and a method for determining downlink communication link parameters based on space-based VDES (vertical data base extended sequences) so as to solve the technical problems of interference and conflict among received signals in a space-based system.
In order to solve the problems, the technical scheme of the invention is as follows:
a system for determining parameters of a space-based VDES downlink communication link based on a satellite and a ground ship platform comprises: the system comprises a system parameter setting module, a satellite-ground distance determining module, a satellite-ground link loss determining module, a satellite transmitting end parameter determining module, a shipway receiving end parameter determining module and a link analyzing module;
the system parameter setting module is in signal connection with the satellite-ground distance determining module and is used for acquiring satellite parameters and communication parameters, wherein the satellite parameters comprise satellite orbit height and number of ground covering beams, and the communication parameters comprise a downlink communication frequency band, downlink PFD constraint, link margin requirement and transmitter power amplifier;
the satellite-ground distance determining module is used for determining satellite-ground coverage ranges, satellite-ground distances under different nadirs and corresponding ground shipway elevation angles, calculating the satellite-ground coverage range through satellite orbit height, calculating the number of ground-ground covered beams to obtain the ground-ground coverage range of each beam, and calculating the satellite-ground distance under each nadir and the elevation angle of the ground shipway through the satellite-ground coverage range and the ground-ground coverage range of each beam;
the satellite-ground link loss determining module is in signal connection with the satellite-ground distance determining module and is used for calculating signal loss between the satellite-ground links according to the downlink communication frequency band and the satellite-ground distances under each nadir angle, and the signal loss comprises the following steps: the free space loss is calculated through the satellite orbit height and the downlink communication frequency band;
the satellite transmitting terminal parameter determining module is respectively in signal connection with the satellite-to-ground link loss determining module and the link analyzing module and is used for calculating transmitting terminal parameters of the satellite according to the number of the ground-to-ground coverage beams, the power amplifier of the transmitter and the number of the ground-to-ground coverage beams;
the slipway receiving end parameter determining module is respectively in signal connection with the satellite-ground link loss determining module and the link analyzing module and is used for determining receiving end parameters of the ground slipway;
the link analysis module is used for receiving the transmitting signals based on the transmitting end parameters and the receiving signals based on the receiving end parameters to respectively calculate actual power flux density and link allowance, and the satellite transmitting end parameter determination module and the shipway receiving end parameter determination module are adjusted and optimized based on the actual power flux density and the link allowance.
Further preferably, the signal loss further includes rain attenuation loss and atmospheric loss, and the satellite-ground link loss determining module is further configured to obtain the rain attenuation loss and the atmospheric loss according to the downlink communication frequency band.
The parameters of the transmitting terminal of the satellite comprise: the number of satellite antenna elements, the satellite antenna element layout, the satellite antenna element gain, and the equivalent omnidirectional radiated power at each nadir angle, wherein,
used for determining the number of the satellite antenna units and the layout of the satellite antenna units according to the earth coverage of each wave beam of the satellite-earth distance determination module,
and the antenna unit gain module is used for determining the satellite antenna unit gain and the equivalent omnidirectional radiation power of each nadir angle according to the number of the ground coverage beams of the system parameter setting module and the transmitter power amplifier.
Wherein, the receiving end parameter of ground berth includes: a receive antenna gain parameter, a G/T value, a receive sensitivity parameter, a system noise figure, and a carrier-to-noise ratio parameter.
Specifically, the link analysis module is configured to calculate a power flux density of each nadir angle according to the equivalent omnidirectional radiation power of each nadir angle and the satellite-ground distance under each nadir angle corresponding to the satellite-ground distance determination module, and to calculate a difference between the power flux density of each nadir angle and a downlink PFD constraint, and modify a transmitting end parameter of the satellite by using the difference;
the link analysis module is also used for calculating the actual signal power, the actual carrier-to-noise ratio or the actual bit-to-noise ratio of the ground ship platform according to the equivalent omnidirectional radiation power and the signal loss of each nadir angle, comparing the actual signal power, the actual carrier-to-noise ratio or the actual bit-to-noise ratio with the receiving sensitivity parameter and the carrier-to-noise ratio parameter respectively to obtain a link margin, and correcting the parameters of the transmitting end of the satellite through the link margin.
The link analysis module is used for optimizing receiving end parameters of the ground shipway by combining the anti-interference performance of the ground shipway, the system complexity and the link allowance.
A method for determining parameters of a downlink communication link based on space-based VDES (vertical double-diffused ES), which is applied to a satellite and a ground ship platform, comprises the following steps:
s1, acquiring satellite parameters and communication parameters, wherein the satellite parameters comprise satellite orbit height and the number of beams covered to the ground, and the communication parameters comprise a downlink communication frequency band, downlink PFD constraint, link margin requirement and transmitter power amplifier;
s2, calculating the satellite earth coverage range through the satellite orbit height, calculating the earth coverage beam number to obtain each beam earth coverage range, and calculating the satellite earth distance and the elevation angle of the ground shipway under each nadir angle through the satellite earth coverage range and each beam earth coverage range;
s3, calculating to obtain free space loss through the satellite orbit height and the downlink communication frequency band, and obtaining rain attenuation loss and atmospheric loss through the downlink communication frequency band so as to obtain signal loss;
s4, acquiring the parameters of the transmitting end of the satellite and the parameters of the receiving end of the ground slipway;
s5: calculating actual power flux density and link margin respectively through a transmitting signal of a transmitting end parameter and a receiving signal of a receiving end parameter, and adjusting and optimizing a satellite transmitting end parameter determining module and a shipway receiving end parameter determining module based on the actual power flux density and the link margin;
and repeating the steps S2 to S5 until the transmitting terminal parameters and the transmitting terminal parameters meet the requirements of the optimal design.
Specifically, the step S4 of acquiring the transmitting end parameters of the satellite specifically includes the following steps:
determining the number of satellite antenna units and the layout of the satellite antenna units through the ground coverage range of each wave beam;
and determining the gain of the satellite antenna unit and the equivalent omnidirectional radiation power of each nadir angle through the number of the ground covering beams and the power amplifier of the transmitter.
Due to the adoption of the technical scheme, compared with the prior art, the invention has the following advantages and positive effects:
1) the space-based VDES downlink communication link parameter determining system provided by the invention adopts a multi-module combined design aiming at the optimization design requirement of multi-beam VDES satellite load, is flexible and convenient, can be suitable for load system design under various satellite orbit and beam requirements, and has better universality.
2) The space-based VDES downlink communication link parameter determining system provided by the invention is closely combined with the requirements of VDES technical specifications and satellite platform requirements, evaluates and analyzes the communication link of each nadir angle, and has better practicability.
3) The design parameters provided by the invention cover a plurality of aspects such as satellite orbits, communication links, satellite load internal designs (including antennas and transmitters) and the like, and have better systematicness.
4) The link analysis module provided by the invention adopts a multivariate comprehensive evaluation strategy, fully considers multiple factors such as anti-interference performance, link margin, system complexity, communication capacity and the like, and has better scientificity.
5) The space-based VDES downlink communication link design and analysis method provided by the invention can support MATLAB, STK and other data interfaces, and has better expandability.
6) The invention can support more users in a limited frequency spectrum by means of a multi-beam covering such a multiplexing mode of Space Division Multiple Access (SDMA); by means of narrow antenna beams covered by multiple beams, the difference of AIS time slot conflict signals can be enhanced, and the time slot conflict resolution capability of the satellite is improved; with DBF technology in multi-beam coverage, the transmit power of the satellite downlink signal can be controlled to avoid or reduce interference to the terrestrial system.
Drawings
Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention.
Fig. 1 is a schematic structural diagram of a system for determining parameters of a downlink communication link based on space-based VDES according to an embodiment of the present invention;
FIG. 2 is a simulated view of the satellite-ground distances corresponding to the nadir angles at different track heights according to an embodiment of the present invention;
FIG. 3 is a simulation of PFD constraints at different nadirs according to an embodiment of the present invention;
FIG. 4 is a simulation diagram of the maximum equivalent omnidirectional radiation power values corresponding to each nadir angle satisfying the PFD constraint at different track heights in accordance with an embodiment of the present invention;
fig. 5 is a simulation diagram of downlink margins corresponding to different modulation schemes satisfying PFD constraints at different track heights according to an embodiment of the present invention;
FIG. 6 is a graph illustrating satellite antenna unit gain simulation according to an embodiment of the present invention;
FIG. 7 is a simulation of satellite beam gain according to an embodiment of the present invention;
FIG. 8 is a graph illustrating satellite antenna synthetic gain simulation according to an embodiment of the present invention;
FIG. 9 is a simulation of downlink margin for different information rates for different flight directions of a satellite in accordance with one embodiment of the present invention;
fig. 10 is a flowchart illustrating a method for determining downlink communication link parameters based on space-based VDES according to an embodiment of the present invention.
Detailed Description
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following description will be made with reference to the accompanying drawings. It is obvious that the drawings in the following description are only some examples of the invention, and that for a person skilled in the art, other drawings and embodiments can be derived from them without inventive effort.
For the sake of simplicity, the drawings only schematically show the parts relevant to the present invention, and they do not represent the actual structure as a product. In addition, in order to make the drawings concise and understandable, components having the same structure or function in some of the drawings are only schematically illustrated or only labeled. In this document, "one" means not only "only one" but also a case of "more than one".
The system and method for determining parameters of a downlink communication link based on space-based VDES according to the present invention will be described in detail with reference to the accompanying drawings and specific embodiments. Advantages and features of the present invention will become apparent from the following description and from the claims.
Example 1
At present, although technical specifications of space-based VDES are still in the process of modification and improvement, technical indexes of a part of physical layers of satellite-ground communication links have definite requirements, so that the relevant technical requirements in the specifications need to be met in the process of optimally designing a load system.
Referring to fig. 1, the present embodiment provides a space-based VDES downlink communication link parameter determination system, which is applied to design of communication link parameters between a satellite and a ground ship platform. Specifically, the system comprises: the system comprises a system parameter setting module, a satellite-ground distance determining module, a satellite-ground link loss determining module, a satellite transmitting end parameter determining module, a shipway receiving end parameter determining module and a link analyzing module. The design of parameters within this embodiment requires that both VDES specification requirements and feasibility requirements for satellite-to-ground downlink engineering implementation be met.
The system parameter setting module is used for determining parameters of a constellation level, namely satellite parameters, such as satellite orbit height and the number of beams covering the ground, and is also used for determining parameters of a physical level, namely communication parameters, determined by technical specifications, such as a downlink communication frequency band, a downlink PFD constraint (PFD-mask), link margin requirements and a transmitter power amplifier of a satellite.
The output end of the system parameter setting module is in signal connection with the receiving end of the satellite-ground distance determining module, the output end of the satellite-ground distance determining module is in signal connection with the receiving end of the satellite-ground link loss determining module, and the satellite-ground distance determining module and the satellite-ground link loss determining module are respectively used for determining the satellite-ground distances and the corresponding link losses of different nadir angles in the satellite coverage range.
Specifically, the satellite-to-ground distance determining module is an intermediate module, and is configured to calculate a satellite-to-ground coverage area according to the satellite orbit height of the system parameter setting module, and calculate a number of ground-to-ground coverage beams according to the calculation to obtain a ground-to-ground coverage area of each beam. The satellite-ground distance determining module needs to traverse all the nadir angles (with variable angle precision) in the coverage range, and calculates the satellite-ground distance under each nadir angle and the elevation angle of the ground shipway according to the satellite-ground coverage range and each beam-ground coverage range.
Referring to fig. 2, in the present embodiment, the basic functions of the satellite-ground distance calculation module are illustrated according to two satellite examples of different orbital altitudes. According to the geometrical relationship between the satellite and the ship, the following information is obtained by utilizing a corresponding formula: under the track height of 900km, the satellite ground coverage range is-61.2 degrees to +61.2 degrees, and the satellite-ground distance variation range of different nadir angles is 900km to 3504 km; under the track height of 1400km, the satellite-to-ground coverage range is-55 degrees to +55 degrees, and the satellite-to-ground distance variation range of different nadir angles is 1400km to 4449 km.
Specifically, referring to fig. 1, the satellite-ground link loss determining module is also an intermediate module, and is configured to calculate signal loss between the satellite-ground links according to the downlink communication frequency band of the system parameter setting module and the satellite-ground distance at each nadir angle determined by the satellite-ground distance determining module, where the signal loss includes: free space loss, rain attenuation loss, atmospheric loss, polarization loss, pointing loss, multiple access loss, and the like. The satellite-ground link loss determining module is used for calculating according to the satellite orbit height and the downlink communication frequency band to obtain free space loss; the satellite-ground link loss determining module is also used for obtaining rain attenuation loss and atmospheric loss according to the downlink communication frequency band; determining pointing loss according to the pointing error; and determining polarization loss, multiple access loss and the like according to engineering experience.
Referring to fig. 1, 3 to 5, in this embodiment, a receiving end of the satellite transmitting end parameter determining module is in signal connection with an output end of the satellite-to-ground link loss determining module, and is configured to calculate a transmitting end parameter of the satellite according to the number of the ground-to-ground coverage beams, the transmitter power amplifier, and the number of the ground-to-ground coverage beams of the system parameter setting module. In this embodiment, the satellite antenna is a multi-beam and multi-element array antenna, and the antenna adopts a DBF system. The transmitting end parameters of the satellite comprise: the satellite antenna unit number, the satellite antenna unit layout, the satellite antenna unit gain and the equivalent omnidirectional radiation power of each nadir angle are used for determining the satellite antenna unit number and the satellite antenna unit layout according to the ground coverage range of each wave beam of the satellite-ground distance determining module; and the antenna unit gain module is used for determining the satellite antenna unit gain and the equivalent omnidirectional radiation power of each nadir angle according to the number of the ground coverage beams of the system parameter setting module and the transmitter power amplifier.
The satellite transmitting terminal parameter determining module determines the satellite transmitting parameters under the constraint condition that the PFD-mask is met. The satellite to ground power flux density PFD is limited by the PFD-mask, i.e. the downlink PFD of the designed satellite communication system cannot be larger than the PFD-mask specified in the VDES specification.
Where θ is the elevation angle from the vessel to the satellite.
According to the ground PFD constraint, determining the EIRP (equivalent isotropic radiated power) of the satellite, and determining the EIRP according to the constraint condition that the PFD is not more than the PFD-mask on the premise that the PFD-mask and the satellite-to-ground distance d are determined. The EIRP value may be used as an input condition for satellite antenna element gain, number of elements, and DBF design. Under the constraint of PFD-mask, according to the determined EIRP, VDES downlink margins corresponding to different track heights and different modulation modes, namely different receiving sensitivities, are calculated. The link margin can be used as an evaluation criterion of the VDES downlink communication link performance.
The slipway receiving end parameter determining module is in signal connection with the satellite-ground link loss determining module and the link analyzing module respectively and is used for determining receiving end parameters of a ground slipway, and the ground slipway adopts a standard slipway antenna. The receiving end parameters of the ground slipway include: and receiving an antenna gain parameter, a G/T value, a receiving sensitivity parameter, a system noise coefficient and a carrier-to-noise ratio parameter, wherein the carrier-to-noise ratio parameter is determined according to the power of the ground ship after receiving the signal.
Referring to fig. 1, the link analysis module is configured to receive a transmission signal based on a transmission end parameter and a reception signal based on a reception end parameter, and respectively calculate an actual power flux density and a link margin. Specifically, the link analysis module is configured to calculate an actual power flux density of each nadir angle according to the equivalent omnidirectional radiation power of each nadir angle and the satellite-ground distance under each nadir angle corresponding to the satellite-ground distance determination module, and to calculate a difference between the power flux density of each nadir angle and a downlink PFD constraint, and modify a transmitting end parameter of the satellite by using the difference;
the link analysis module is also used for calculating the actual signal power, the actual carrier-to-noise ratio or the actual bit-to-noise ratio of the ground ship platform according to the equivalent omnidirectional radiation power and the signal loss of each nadir angle, comparing the actual signal power, the actual carrier-to-noise ratio or the actual bit-to-noise ratio with the receiving sensitivity parameter and the carrier-to-noise ratio parameter respectively to obtain a link margin, and correcting the parameters of the transmitting end of the satellite through the link margin. In addition, the link analysis module is used for optimizing receiving end parameters of the ground ship platform by combining the anti-interference performance, the system complexity and the link allowance of the ground ship platform, wherein the anti-interference performance is obtained by PFD constraint of a ground ship platform antenna, and the system complexity is obtained by comprehensively considering the number of satellites in communication with the ground ship platform, the number of ground-to-ground coverage beams and channels of a single satellite, the satellite-borne antenna scale and the like.
Referring to fig. 6 to 9, the specific conclusion of the present embodiment is as follows: when the satellite adopts eight antenna units, 2 and 4 beams are formed in the flight direction of the satellite and the vertical flight direction of the satellite respectively, namely 8 beams are formed in total in the ground coverage area. Analyzing the link margins corresponding to three data formats (LCIDs 25, 26, and 27) of VDES can obtain: in the flight direction, the downlink margin of a data format LCID 27(50.4kbps) in a range of-2 degrees to +2 degrees at a bottom of the day is less than 3dB, and the downlink margin of the data format and the bottom of the day are both more than 3 dB; in the vertical flight direction, the downlink margins of various data formats are all larger than 3dB in the range of-45 degrees to +45 degrees nadir angles covered by the satellite. The slipway receive sensitivity is required to be better than-112 dBm over the entire coverage area.
Example 2
Referring to fig. 10, this embodiment provides a method for determining parameters of a space-based VDES downlink communication link according to embodiment 1, where the method employs a system for determining parameters of a space-based VDES downlink communication link according to embodiment 1, and a satellite and a ground ship platform use the method for determining parameters of a space-based VDES downlink communication link, and the method includes the following steps:
in step S1, a satellite parameter and a communication parameter are input into the system, where the satellite parameter includes a satellite orbit height and a number of beams covering the ground, and the communication parameter includes a downlink communication frequency band, a downlink PFD constraint (PFD-mask), a link margin requirement, a transmitter power amplifier, an information rate, a modulation mode thereof, and a working bandwidth. The parameters belong to initial parameters and are required to meet the technical specification requirements of VDES.
In step S2, the satellite-ground distance calculation module calculates the satellite-ground coverage area through the satellite orbit height, calculates the number of the ground-ground coverage beams to obtain the ground-ground coverage area of each beam, and calculates the satellite-ground distance and the elevation angle of the ground ship platform under each nadir angle through the satellite-ground coverage area and each beam-ground coverage area;
in step S3, the satellite-ground link loss calculation module calculates the free space loss through the satellite orbit height and the downlink communication frequency band, and obtains the rain attenuation loss and the atmospheric loss through the downlink communication frequency band, thereby obtaining the signal loss;
in step S4, the satellite transmitting end parameter determining module needs to determine parameters including the number of satellite antenna elements, the layout of the antenna elements, the gain of the antenna elements, the antenna synthesis gain, the power amplifier design, and the EIRP, i.e., the equivalent omnidirectional radiation power. Determining the number of satellite antenna units and the layout of the satellite antenna units according to the ground coverage of each wave beam; the gain of the satellite antenna unit and the EIRP of each nadir angle are determined by the number of the ground-covering beams and the power amplifier of the transmitter.
In addition, the receiving end parameter determining module of the ship platform needs to determine receiving end parameters of the ground ship platform, and the receiving end parameters include antenna gain, G/T value, receiving sensitivity, carrier-to-noise ratio design and other functions. Part of the parameters of the receiving end of the ship platform need to meet the requirements of VDES technical specifications.
In step S5, an actual power flux density and a link margin are calculated respectively from the transmission signal of the transmission end parameter and the reception signal based on the reception end parameter, and the satellite transmission end parameter determination module and the slipway reception end parameter determination module are adjusted and optimized based on the actual power flux density and the link margin; and repeating the steps S2 to S5 until the transmitting end parameters and the transmitting end parameters meet the requirements of the optimal design.
The embodiments of the present invention have been described in detail with reference to the accompanying drawings, but the present invention is not limited to the above embodiments. Even if various changes are made to the present invention, it is still within the scope of the present invention if they fall within the scope of the claims of the present invention and their equivalents.
Claims (8)
1. A space-based VDES downlink communication link parameter determination system using a satellite and a ground ship, comprising: the system comprises a system parameter setting module, a satellite-ground distance determining module, a satellite-ground link loss determining module, a satellite transmitting end parameter determining module, a shipway receiving end parameter determining module and a link analyzing module;
the system parameter setting module is in signal connection with the satellite-ground distance determining module and is used for acquiring satellite parameters and communication parameters, wherein the satellite parameters comprise satellite orbit height and number of ground covering beams, and the communication parameters comprise a downlink communication frequency band, downlink PFD constraint, link margin requirement and transmitter power amplifier;
the satellite-ground distance determining module is used for determining satellite-ground coverage, satellite-ground distances under different nadirs and corresponding ground shipway elevation angles, calculating the satellite-ground coverage through the satellite orbit height, calculating the number of the ground coverage beams to obtain each beam-ground coverage, and calculating the satellite-ground distance under each nadir and the elevation angle of the ground shipway through the satellite-ground coverage and each beam-ground coverage;
the satellite-ground link loss determining module is in signal connection with the satellite-ground distance determining module, and is configured to calculate, according to the downlink communication frequency band and the satellite-ground distances at various nadir angles, signal loss between satellite-ground links, where the signal loss includes: the free space loss is calculated through the satellite orbit height and the downlink communication frequency band;
the satellite transmitting terminal parameter determining module is respectively in signal connection with the satellite-to-ground link loss determining module and the link analyzing module and is used for calculating transmitting terminal parameters of the satellite according to the number of the ground-to-ground coverage beams, the transmitter power amplifier and the number of the ground-to-ground coverage beams;
the slipway receiving end parameter determining module is respectively in signal connection with the satellite-ground link loss determining module and the link analyzing module and is used for determining receiving end parameters of the ground slipway;
the link analysis module is used for receiving the transmitting signals based on the transmitting end parameters and the receiving signals based on the receiving end parameters to respectively calculate actual power flux density and link margin, and the satellite transmitting end parameter determination module and the slipway receiving end parameter determination module are adjusted and optimized based on the actual power flux density and the link margin.
2. The space-based VDES downlink communication link parameter determination system of claim 1, wherein the signal loss further comprises a rain attenuation loss and an atmospheric loss, and the satellite-to-ground link loss determination module is further configured to obtain the rain attenuation loss and the atmospheric loss according to the downlink communication frequency band.
3. The space-based VDES downlink communication link parameter determination system according to claim 2, wherein said satellite transmitting side parameters comprise: the number of satellite antenna elements, the satellite antenna element layout, the satellite antenna element gain, and the equivalent omnidirectional radiated power at each nadir angle, wherein,
for determining the number of the satellite antenna units and the layout of the satellite antenna units according to the earth-to-earth coverage of each beam of the satellite-to-earth distance determination module,
and the antenna unit is used for determining the gain of the satellite antenna unit and the equivalent omnidirectional radiation power of each nadir angle according to the number of the ground covering beams of the system parameter setting module and the transmitter power amplifier.
4. The space-based VDES downlink communication link parameter determination system according to claim 3, wherein the receiving end parameters of the ground ship platform comprise: receiving antenna gain parameters, G/T values, system noise coefficients, receiving sensitivity parameters and carrier-to-noise ratio parameters.
5. The space-based VDES downlink communication link parameter determining system according to claim 4, wherein the link analyzing module is configured to calculate a power flux density of each nadir angle according to the equivalent omnidirectional radiation power of each nadir angle and a satellite-to-ground distance under each nadir angle corresponding to the satellite-to-ground distance determining module, calculate a difference between the power flux density of each nadir angle and the downlink PFD constraint, and modify a transmitting end parameter of the satellite by using the difference;
the link analysis module is further configured to calculate an actual signal power, an actual carrier-to-noise ratio or an actual bit-to-noise ratio of the ground ship platform according to the equivalent omnidirectional radiation power and the signal loss at each nadir angle, compare the actual signal power, the actual carrier-to-noise ratio or the actual bit-to-noise ratio with the receiving sensitivity parameter and the carrier-to-noise ratio parameter respectively to obtain a link margin, and correct a transmitting terminal parameter of the satellite through the link margin.
6. The system of claim 5, wherein the link analysis module is configured to optimize receiving end parameters of the ground ship platform in combination with the anti-interference performance and system complexity of the ground ship platform and the link margin.
7. A method for determining parameters of a downlink communication link based on a space-based VDES (vertical double-diffused ES) is characterized in that a satellite and a ground ship platform apply the method for determining the parameters of the downlink communication link based on the space-based VDES, and comprises the following steps:
s1, acquiring satellite parameters and communication parameters, wherein the satellite parameters comprise satellite orbit height and the number of beams covered to the ground, and the communication parameters comprise a downlink communication frequency band, downlink PFD constraint, link margin requirement and transmitter power amplifier;
s2, calculating the satellite earth coverage range through the satellite orbit height, calculating the earth coverage range of each beam through the earth coverage beam number, and calculating the earth distance under each nadir angle and the elevation angle of the ground shipway through the satellite earth coverage range and each beam earth coverage range;
s3, calculating to obtain free space loss through the satellite orbit height and the downlink communication frequency band, and obtaining rain attenuation loss and atmospheric loss through the downlink communication frequency band so as to obtain signal loss;
s4, acquiring the transmitting end parameters of the satellite and the receiving end parameters of the ground shipway;
s5: calculating actual power flux density and link margin respectively through the transmitting signal of the transmitting end parameter and the receiving signal of the receiving end parameter, and adjusting and optimizing the satellite transmitting end parameter determining module and the shipway receiving end parameter determining module based on the actual power flux density and the link margin;
repeating the steps S2 to S5 until the transmitting end parameters and the receiving end parameters meet the requirements of optimal design.
8. The method for determining parameters of a space-based VDES downlink communication link according to claim 7, wherein the step S4 of obtaining the parameters of the transmitting end of the satellite includes the following steps:
determining the number of the satellite antenna units and the layout of the satellite antenna units through the coverage range of each wave beam to the ground;
and determining the gain of the satellite antenna unit and the equivalent omnidirectional radiation power of each nadir angle through the number of the ground covering beams and the power amplifier of the transmitter.
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