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KR-102962426-B1 - System and method for determining the orientation of an electronically steerable antenna

KR102962426B1KR 102962426 B1KR102962426 B1KR 102962426B1KR-102962426-B1

Abstract

The determination of the set physical orientation of an electronically steerable satellite antenna using signals received from the satellite antenna is described. The set physical orientation of the satellite antenna may be fixed relative to the antenna. In turn, the antenna can determine the direction of incidence of signals by scanning a beam through an angular range to measure the signal strength of signals from transmitters (e.g., satellites). The direction of incidence of signals from corresponding known orbital positions of the satellites enables the satellite antenna to determine the set physical orientation with higher precision. Specifically, high precision allows the avoidance angle for non-target satellites to be minimized, thereby enabling more efficient antenna operation with fewer interference mitigation actions.

Inventors

  • 부어 케네스 브이.

Assignees

  • 비아셋, 인크

Dates

Publication Date
20260511
Application Date
20210308

Claims (20)

  1. A method for determining the set physical orientation of an electronically steerable satellite antenna (120) for use in a satellite communication system, A step of determining the position of the above-mentioned electronically steerable satellite antenna (120) with respect to the Earth; A step of receiving signals (514), (516) from each of at least two different satellites (510), (512); A step of determining the incident direction of each of the signals (514), (516) for the aiming direction (240) of the electronically steerable satellite antenna (120) by electronically steering the beam of the electronically steerable satellite antenna (120); and The method comprises the step of calculating a set physical orientation of the electronically steerable satellite antenna (120) with respect to the Earth based on the position of the electronically steerable satellite antenna (120) and the incident direction of each of the signals (514), (516) from the satellites (510), (512) where the signals (514), (516) are received, wherein the satellites (510), (512) are in known orbital positions with respect to the Earth, and the set physical orientation includes an azimuth (234), an elevation (232), and a rotation of the aiming direction (240) of the electronically steerable satellite antenna (120) with respect to the Earth; A method comprising the step of determining the incident direction of each of the signals (516)(514) for the aiming direction (240) of the electronically steerable satellite antenna (120), wherein the step comprises electronically steering the beam of the electronically steerable satellite antenna (120) to scan over an azimuth range and an elevation range.
  2. As a method for mitigating interference between an electronically steerable satellite antenna (120) and a non-target satellite (112), A step of determining the position of the above-mentioned electronically steerable satellite antenna (120) with respect to the Earth; A step of receiving signals (514), (516) from each of at least two different satellites (510), (512); A step of determining the incident direction of each of the signals (514), (516) for the aiming direction (240) of the electronically steerable satellite antenna (120) by electronically steering the beam of the electronically steerable satellite antenna (120); A step of calculating a set physical orientation of the electronically steerable satellite antenna (120) with respect to the Earth based on the position of the electronically steerable satellite antenna (120) and the incident direction of each of the signals (514), (516) from the satellites (510), (512) ― the satellites (510), (512) receiving the signals (514), (516) are in known orbital positions with respect to the Earth, and the set physical orientation includes an azimuth (234), elevation (232), and rotation of the aiming direction (240) of the electronically steerable satellite antenna (120) with respect to the Earth ―; A step of determining a beam pattern emission profile for the above electronically steerable satellite antenna (120); A step of associating the above beam pattern emission profile with the above-set physical orientation of the above-mentioned electronically steerable satellite antenna (120); A step of detecting an interference event based on the beam pattern emission profile for the electronically steerable satellite antenna (120) in the above-set physical orientation ― said interference event includes the emission from the electronically steerable satellite antenna (120) reaching a predetermined level for a non-target satellite (112) ―; and A method comprising the step of modifying the transmission of the electronically steerable satellite antenna (120) in response to the above interference event.
  3. A method in which, in paragraph 2, the beam pattern emission profile is asymmetric.
  4. In either paragraph 2 or 3, A method further comprising the step of steering the beam of the electronically steerable satellite antenna (120) to communicate a signal between the electronically steerable satellite antenna (120) and the target satellite (110).
  5. A method according to paragraph 4, wherein the interference event is based on the side lobe (726a) emission other than the main beam (722) emission of the beam pattern emission profile.
  6. In paragraph 4, the method is such that the interference event is for a non-target satellite (712) geosynchronous orbit.
  7. In paragraph 4, the method wherein the interference event is for a non-target satellite (712) in low earth orbit.
  8. In paragraph 4, the method wherein the electronically steerable satellite antenna (120) comprises a phase array satellite antenna (220).
  9. A method according to claim 1, wherein the incident direction of each of the signals (514, 516) is determined based on the signal strength indicator of the signal with respect to the azimuth range and the elevation range.
  10. A method according to claim 1, wherein at least one of the two different satellites (510, 512) comprises a geostationary satellite.
  11. A method according to claim 1, wherein at least one of the two different satellites (510, 512) comprises a low Earth orbit satellite, and the known orbital position with respect to the Earth is based on the ephemeris data of the low Earth orbit satellite at a time reference corresponding to the reception of a signal from the low Earth orbit satellite.
  12. A method according to claim 1, wherein the step of calculating the set physical orientation includes the step of resolving the azimuth angle (234), the elevation angle (232), and the rotation within an error of about 1 degree or less.
  13. A system operable to determine the set physical orientation of an electronically steerable satellite antenna (120) for use in a satellite communication system, Electronically steerable satellite antenna (120) ― the electronically steerable satellite antenna (120) electronically steers the beam of the electronically steerable satellite antenna (120) to receive signals (514), (516) from each of at least two different satellites (510), (512) ―; A position module (314) for determining the position of the above-mentioned electronically steerable satellite antenna (120) with respect to the Earth; and An orientation calculation module (312) for determining the incident direction of each of the signals (514, 516) for the aiming direction (240) of the electronically steerable satellite antenna (120) by considering the known orbital positions of the satellites (510, 512) with respect to the Earth, and calculating a set physical orientation of the electronically steerable satellite antenna (120) with respect to the Earth based on the position of the electronically steerable satellite antenna (120) and the incident direction of each of the signals (514), (516) — wherein the set physical orientation includes an azimuth (234), an elevation (232), and a rotation of the aiming direction (240) of the electronically steerable satellite antenna (120) with respect to the Earth — The above orientation calculation module (312) determines the incident direction of each of the signals (514)(516) for the aiming direction (240) of the electronically steerable satellite antenna (120) by electronically steering the beam of the electronically steerable satellite antenna (120) to scan over an azimuth range and an elevation range to identify the incident direction.
  14. A system capable of operating to mitigate interference between an electronically steerable satellite antenna (120) and a non-target satellite (112), Electronically steerable satellite antenna (120) ― the electronically steerable satellite antenna (120) electronically steers the beam of the electronically steerable satellite antenna (120) to receive signals (514), (516) from each of at least two different satellites (510), (512) ―; A position module (314) for determining the position of the above-mentioned electronically steerable satellite antenna (120) relative to the Earth; An orientation calculation module (312) for determining the incident direction of each of the signals (514, 516) for the aiming direction (240) of the electronically steerable satellite antenna (120) by considering the known orbital positions of the satellites (510, 512) with respect to the Earth, and calculating a set physical orientation of the electronically steerable satellite antenna (120) with respect to the Earth based on the position of the electronically steerable satellite antenna (120) and the incident direction of each of the signals (514), (516) — wherein the set physical orientation includes an azimuth (234), an elevation (232), and a rotation of the aiming direction (240) of the electronically steerable satellite antenna (120) with respect to the Earth — The above electronically steerable satellite antenna (120) includes a beam pattern emission profile, and the orientation calculation module (312) associates the beam pattern emission profile with the set physical orientation of the electronically steerable satellite antenna (120). A scheduler (330) for detecting an interference event based on the beam pattern emission profile for the electronically steerable satellite antenna (120) in the above-set physical orientation ― the interference event includes the emission from the electronically steerable satellite antenna (120) reaching a predetermined level for a non-target satellite (112); The above electronically steerable satellite antenna (120) is a system that modifies transmission in response to the interference event.
  15. A system in which, in paragraph 14, the beam pattern emission profile is asymmetric.
  16. In Paragraph 14, The above electronically steerable satellite antenna (120) steers the beam of the above electronically steerable satellite antenna (120) to communicate a signal between the above electronically steerable satellite antenna (120) and the target satellite (110), in a system.
  17. A system according to claim 16, wherein the interference event is based on the side lobe (726a) emission other than the main beam (722) emission of the beam pattern emission profile.
  18. A system in which, in any one of clauses 16 to 17, the interference event is for a non-target satellite (712) in a geosynchronous orbit.
  19. A system in which, in any one of clauses 16 to 17, the interference event is for a non-target satellite (712) in low Earth orbit.
  20. In claim 19, the system wherein the electronically steerable satellite antenna (120) comprises a phase array satellite antenna (220).

Description

System and method for determining the orientation of an electronically steerable antenna Satellite communication systems, including satellites in geosynchronous Earth orbit (GEO), can enable communication between user terminals on Earth and GEO satellites. GEO satellites have an orbital period identical to the Earth's rotation period. As such, GEO satellites can be geosynchronous or quasi-geosynchronous, so they generally appear to be stationary or circulating with a very limited range of movement in the sky relative to the user terminal. In the case of geosynchronous GEO satellites, the orbit is located just above the Earth's equator. Accordingly, the pointing of the satellite antenna on the user terminal can be fixed without the need to reorient or change the antenna's direction, making the satellite antenna pointing relatively simple. Furthermore, because the satellite antenna's pointing is fixed, it can be indifferent to interference with other satellites. However, since GEO satellites in geosynchronous orbits are located above the equator, a limited number of "slots" or spatial availability are available in geosynchronous orbits. Additionally, because GEO satellites are at relatively high altitudes, they cause high latency in signals transmitted between the Earth and the GEO satellites. Such high latency is particularly disadvantageous in the context of certain time-sensitive data. As a result of the unavailability of geosynchronous orbit slots, the desire to provide a satellite communication system with reduced latency, and other constraints on GEO satellites, satellite communication systems may additionally or alternatively use low Earth orbit (LEO) or mid-Earth orbit (MEO) satellites to enable communication with user terminals. LEO and MEO satellites and/or orbits may be collectively referred to herein as non-geosynchronous (non-GEO). Because non-GEO satellites have orbital periods that are not identical to the Earth's rotation period, they do not appear to be stationary in the sky relative to the user terminal. User terminals for communication with non-GEO satellites typically employ a form of tracking that allows the satellite antenna to target the non-GEO satellite as it passes through the sky relative to the user terminal via the user terminal's satellite antenna and/or the movement of the satellite antenna's beam. While tracking capability adds complexity to the user terminal, the ability to use non-GEO satellites for communication with the user terminal provides advantages that correspond to the added complexity of the user terminal. However, the disadvantages regarding the use of non-GEO satellites are preferably mitigated. In particular, when tracking a non-GEO satellite using the user terminal's satellite antenna, it may be desirable to avoid interference with other satellites present in the sky relative to the user terminal (e.g., to maintain operational status or avoid violations of authorization systems). The present disclosure relates to determining the orientation of an electronically steerable antenna relative to the Earth, for example, to more precisely determine the interference angle with respect to non-target satellites to help more efficiently avoid interference with non-target satellites. The present invention enables the orientation of an electronically steerable antenna to be resolved with a high level of accuracy and precision. As such, user terminal operations can experience improved performance through reduced interference mitigation operations. Specifically, through precise orientation determination, the radiation pattern of the satellite antenna is precisely modeled, so that the error margin regarding the avoidance angle with respect to non-target satellites with respect to the user terminal's satellite antenna can be reduced. The present disclosure generally determines the set physical orientation of an electronically steerable satellite antenna based on triangulation using signals received from a plurality of transmitters (e.g., one or more satellites). By determining the incident direction of the signals received from the plurality of transmitters, the antenna system can resolve the set physical orientation of the antenna. Since the reception of these signals can be performed autonomously by the antenna system, the set mental orientation can be resolved without the intervention of a user or technician (e.g., without the user needing to physically measure the orientation of the antenna). With the foregoing in mind, the present disclosure facilitates determining the set physical orientation of an electronically steerable satellite antenna for use in a satellite communication system. The present disclosure includes determining the position of an electronically steerable satellite antenna relative to the Earth. A plurality of signals are received from at least two different angular satellites located at known orbital positions relative to the Earth. For clarification, a pl