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Multi-beam pointing on-orbit calibration method suitable for high-throughput satellite

A multi-beam, high-throughput technology, applied in the field of satellite communication, can solve the problems of inability to meet the multi-beam on-orbit pointing accuracy requirements and high precision, and achieve fast tracking speed and good real-time performance

Active Publication Date: 2019-10-11
CHINA ACADEMY OF SPACE TECHNOLOGY
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Problems solved by technology

[0004] The technical problem solved by the present invention is: in view of the current prior art, due to high-throughput satellite multi-beam antenna pointing accuracy requirements are high, the antenna pointing accuracy guaranteed by the traditional open-loop driving method cannot meet the multi-beam on-orbit pointing accuracy requirements, a multi-beam pointing on-orbit calibration method suitable for high-throughput satellites is proposed

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  • Multi-beam pointing on-orbit calibration method suitable for high-throughput satellite
  • Multi-beam pointing on-orbit calibration method suitable for high-throughput satellite
  • Multi-beam pointing on-orbit calibration method suitable for high-throughput satellite

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Embodiment Construction

[0047] A multi-beam pointing on-orbit calibration method suitable for high-throughput satellites, aiming at the current situation that high-throughput satellites adopt multi-beam design and narrow beam width, and the coverage gain is easily affected by pointing deviation. The on-orbit calibration system of antennas, radio frequency channels, tracking receivers, antenna controllers, and antenna drive mechanisms calibrates the antennas in the selected coverage areas, and realizes the calibration of multi-aperture and multi-beam antennas to meet the requirements of the system for seamless alignment of beams. Coverage and its coverage area gain requirements.

[0048] After the antenna to be calibrated is selected by the on-orbit calibration system, the signal sent by the ground beacon station is received through the calibration feed in the antenna to be calibrated, converted into a control command in the tracking receiver, and the antenna drive mechanism is driven by the antenna co...

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Abstract

The invention discloses a multi-beam pointing on-orbit calibration method suitable for a high-throughput satellite. A satellite-borne on-orbit calibration system comprising an antenna to be calibrated, a radio frequency channel, a tracking receiver, an antenna controller and an antenna driving mechanism is used; a single-pulse tracking system is adopted; and aiming at the current situation that the high-throughput satellite adopts a multi-beam design, the beam width is relatively narrow and the gain of a coverage area is easily influenced by a pointing deviation, a calibration signal of a ground beacon station is received, and antenna beam pointing is subjected to closed-loop automatic correction, so that multi-caliber multi-beam antenna pointing is calibrated, and the requirements of thesystem on beam seamless coverage and the gain of the coverage area of the satellite are met.

Description

technical field [0001] The invention relates to a multi-beam pointing on-orbit calibration method suitable for high-throughput satellites, which belongs to the technical field of satellite communication. Background technique [0002] The multi-beam ground coverage characteristics of high-throughput satellites are generated by the alternate arrangement of multiple feeds in the reflector to achieve seamless coverage. However, the beam width generated by each reflector is narrow. Errors will cause a certain deviation between the beams generated by each reflector and the design, which will have a greater impact on the seamless coverage of the final system beams. At the same time, if the antenna works according to the uncalibrated state of the beam, it will reduce the gain of the coverage area and deteriorate the C / I of the same-frequency beam, which will affect the final use of the system in severe cases. Therefore, in order to meet the requirements of the system for seamless b...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): H01Q3/08H01Q3/00
CPCH01Q3/005H01Q3/08
Inventor 杨清龙李殷乔尹伟臻李静涛杨显强
Owner CHINA ACADEMY OF SPACE TECHNOLOGY
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