Circular orbit low orbit satellite zenith pass remaining visible duration prediction method

Abstract

The invention discloses a circular orbit low orbit satellite zenith pass remaining visible duration prediction method. According to the method, operation work characteristics of a satellite are fully used; the spatial position of the satellite and corresponding time information are constantly calculated and updated; the information is broadcasted to a user on the ground in the form of a simple navigation signal; after the user on the ground receives the navigation signal, clock calibration and user positioning are carried out through a GPS receiving device; the elevation angle and the track angle of the satellite relative to the user are calculated in real time; and satellite zenith pass remaining visible duration is solved; the method is simple and effective; less navigation signal content is needed; the degree of dependence on satellite ephemeris is low; and on the premise of accurate and timely prediction duration, the hardware cost of the user is not increased.

Description

technical field [0001] The invention relates to the field of satellite communication, in particular to a method for predicting the remaining visible duration of a circular-orbit low-orbit satellite overhead. Background technique [0002] Circular-orbit low-orbit satellites refer to satellites whose orbit is a circular orbit centered on the center of the earth and whose orbital altitude is between 500 kilometers and 2,000 kilometers. This kind of circular-orbit low-orbit satellite has the advantages of small propagation delay, low requirements for terminal equipment antenna size and power consumption, and low satellite launch cost, but the lower the satellite altitude, the smaller its coverage area. Through the ground satellite terminal The time the user is in the air, that is, the overhead time is shorter, so it often requires a network of multiple low-orbit satellites to meet the user's communication needs. [0003] When circular-orbit low-orbit satellites are used for com...

AI Technical Summary

Problems solved by technology

[0005] The technical problem mainly solved by the present invention is to provide a method for predicting the remaining visible duration of a low-orbit satellite in a circular orbit, which solves the problems of over-reliance on satellite ephemeris, high computational complexity, and poor real-time performance in the prior art.

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