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CN-122001445-A - Calculation method, device and storage medium of VDES load coverage area

CN122001445ACN 122001445 ACN122001445 ACN 122001445ACN-122001445-A

Abstract

The application discloses a calculation method, a device, a storage medium and calculation equipment of a satellite VDES load coverage area, wherein the method comprises the steps of determining the position and the gesture of a satellite according to the number of orbits of the satellite, the appointed time and the working mode of the satellite; determining the orientation of a VDES antenna based on the position and the attitude of the satellite and the load installation parameters, constructing a polar plane of the satellite relative to the surface of an earth ellipsoid based on the orientation of the VDES antenna, determining a parameter equation of a space ellipse where the polar plane intersects with the surface of the earth ellipsoid, traversing angle parameters in the space ellipse according to the parameter equation to obtain a tangent point track and an intersection point track, and calculating the load coverage area of the VDES antenna based on the tangent point track and the intersection point track. The application solves the technical problem of difficult calculation of the VDES load coverage area in the prior art.

Inventors

  • LI YUNWEI

Assignees

  • 北京星绘空间信息科技有限公司

Dates

Publication Date
20260508
Application Date
20260128

Claims (10)

  1. 1. A method for calculating a satellite VDES payload coverage area, the method comprising: Determining the position and the attitude of the satellite according to the number of the orbits of the satellite, the designated time and the working mode of the satellite; Determining a VDES antenna pointing direction based on the satellite's position and attitude, and the load-mounting parameters; Determining a parameter equation of a space ellipse intersecting the polar plane and the surface of the earth ellipsoid based on the polar plane of the VDES antenna pointing construction satellite with respect to the surface of the earth ellipsoid; Traversing the angle parameters in the space ellipse according to the parameter equation to obtain a tangent point track and an intersection point track; and calculating the load coverage area of the VDES antenna based on the tangent point track and the intersection point track.
  2. 2. The method of claim 1, wherein determining the position and attitude of the satellite based on the number of orbits of the satellite, the specified time of day, and the satellite mode of operation comprises: Calculating the position and the speed of the satellite according to the number of the orbits, and determining an orbit coordinate system of the satellite according to the position and the speed; and determining the attitude of the satellite according to the satellite working mode, and then determining the body coordinate system of the satellite.
  3. 3. The method of claim 1, wherein said determining a VDES antenna pointing based on the satellite's position and attitude, load installation parameters, comprises: determining the VDES antenna pointing direction based on the position and attitude of the satellite and the VDES antenna mounting angle in the load mounting parameters.
  4. 4. The method of claim 1, wherein the determining a parametric equation for a spatial ellipse where the polar plane intersects the earth ellipsoidal surface comprises: the parameter equation of the space ellipse is M+A cos (t) +Bsin (t), wherein M, A, B is the three-dimensional vector of the center point, the long axis and the short axis of the space ellipse, and t is the angle around the center of the ellipse.
  5. 5. The method of claim 1, wherein traversing the angular parameters in the spatial ellipse according to the parametric equation obtains a tangent point trajectory and an intersection point trajectory, comprising: According to the parameter equation, the angle parameter is from 0 to 2 pi, and the antenna included angle delta of the preset point Q is calculated as follows: δ=arccos(normalize(directVDESAnn),normalize(Q-posSat)); wherein DIRECTVDESANN is the direction of the VDES antenna at the current time, posSat is the position of the satellite at the current time, both of which are located in the earth-fixed system ECEF; Judging whether the antenna included angle delta is smaller than half of an effective beam angle, if yes, determining that the point Q is a tangent point, adding the tangent point into a tangent point array, taking the tangent point array as the tangent point track, if not, calculating a conical busbar at the current moment, calculating an intersection point of the conical busbar and the earth ellipsoid, adding the intersection point into an intersection point array, and taking the intersection point array as the intersection point track.
  6. 6. The method of claim 5, wherein the step of determining the position of the probe is performed, Before adding the tangential points to the tangential point array, performing anti-meridian processing on the tangential points; Before adding the intersection point to the intersection point array, the method further comprises the step of carrying out anti-meridian processing on the intersection point.
  7. 7. The method of claim 5, wherein adding the tangent point to a tangent point array, adding the intersection point to an intersection point array, further comprises: if the intersection point is added first, and then the tangent point is added, resetting the insertion position of the intersection point array to be the head position; And if the tangent point is added first, and then, when the intersecting point is added, resetting the insertion position of the tangent point array to be the head position.
  8. 8. The method according to any one of claims 5 to 7, wherein said calculating a VDES antenna load coverage area based on said tangent point trajectory and said intersection point trajectory comprises: And connecting points in the tangent point array and the intersection point array to serve as boundaries of a load coverage area of the VDES antenna at the current moment.
  9. 9. A computing device for satellite VDES payload coverage, the device comprising: the attitude determination module is used for determining the position and the attitude of the satellite according to the orbit number of the satellite, the designated moment and the satellite working mode; The direction determining module is used for determining the direction of the VDES antenna based on the position and the gesture of the satellite and the load installation parameters; The construction module is used for determining a parameter equation of a space ellipse intersecting the polar plane and the surface of the earth ellipsoid based on the polar plane of the VDES antenna pointing construction satellite relative to the surface of the earth ellipsoid; The track acquisition module is used for traversing the angle parameters in the space ellipse according to the parameter equation to acquire a tangent point track and an intersection point track; and the area calculation module is used for calculating the load coverage area of the VDES antenna based on the tangent point track and the intersection point track.
  10. 10. A storage medium comprising a stored program, wherein the program, when run, controls a device in which the storage medium is located to perform the method of any one of claims 1-8.

Description

Calculation method, device and storage medium of VDES load coverage area Technical Field The application relates to the technical field of satellite communication, in particular to a method and a device for calculating a VDES load coverage area and a storage medium. Background The very high frequency data exchange system (VHF Data Exchange System, VDES for short) is a ship Automatic Identification System (AIS) reinforcing and upgrading system, integrates the existing AIS function, and adds special application message (ASM) and broadband very high frequency data exchange (VDE) functions, can effectively relieve the pressure of the existing AIS data communication, meets the requirements of all data exchange services of ship-to-ship, ship-to-shore, ship-to-satellite and shore-to-satellite, and belongs to a third-generation maritime communication system. This system is also highly approved by IMO (international maritime organization). VDES will become a minority of offshore narrowband satellite communication systems with global unification standards that can fall legally across countries. Thus, a mature and reliable VDES satellite constellation is established and operated, which is critical to future global offshore communications. The low orbit satellites that make up the VDES satellite constellation are in rapid motion and the coverage area of their VDES payload is also moving continuously. The operation center focuses on the coverage area of each satellite at the appointed time so as to prepare for the communication process, such as the satellite or the terminal ends dormancy, adjusts the gesture, opens the radio frequency switch and the like, and the coverage area forecast can also estimate the communication time and better allocate resources and the like. The coverage area referred to herein, using different coverage models may yield different results, The coverage model that is commonly used is a cone with the central axis of the VDES antenna as the central axis, and the VDES antenna is generally mounted in a tilt manner on the satellite. In this case, calculation of the VDES load coverage area is extremely difficult due to the change in orbit attitude of the low-orbit satellite and the different installation angles of the VDES antennas. Aiming at the technical problem that the coverage area is difficult to calculate in the prior art, no effective solution is proposed at present. Disclosure of Invention The embodiment of the application provides a method, a device and a storage medium for calculating a VDES load coverage area, which are used for at least solving the technical problem of difficulty in calculating the VDES load coverage area in the prior art. According to an aspect of an embodiment of the present application, there is provided a method for calculating a satellite VDES load coverage area, including: Determining the position and the attitude of the satellite according to the number of the orbits of the satellite, the designated time and the working mode of the satellite; Determining a VDES antenna pointing direction based on the satellite's position and attitude, and the load-mounting parameters; Determining a parameter equation of a space ellipse intersecting the polar plane and the surface of the earth ellipsoid based on the polar plane of the VDES antenna pointing construction satellite with respect to the surface of the earth ellipsoid; Traversing the angle parameters in the space ellipse according to the parameter equation to obtain a tangent point track and an intersection point track; and calculating the load coverage area of the VDES antenna based on the tangent point track and the intersection point track. On the basis of any one of the above embodiments, the determining the position and the posture of the satellite according to the number of orbits of the satellite, the designated time and the satellite working mode includes: Calculating the position and the speed of the satellite according to the number of the orbits, and determining an orbit coordinate system of the satellite according to the position and the speed; and determining the attitude of the satellite according to the satellite working mode, and then determining the body coordinate system of the satellite. On the basis of any one of the above embodiments, the determining the VDES antenna pointing direction based on the position and the attitude of the satellite and the load installation parameters includes: Determining the VDES antenna pointing direction based on the position and attitude of the satellite and the VDES antenna mounting angle in the load mounting parameters. . On the basis of any one of the above embodiments, the parameter equation for determining a spatial ellipse where the polar plane intersects the earth ellipsoidal surface includes: The parameter equation of the space ellipse is M+A cos (t) +Bsin (t), wherein M, A, B is the three-dimensional vector of the center point, the long axis and the short axis