Satellite terminal beam selection method based on position information and motion trend
A technology of position information and movement trend, applied in the field of satellite mobile communication, can solve the problems of not considering the influence of terminal residence time, only considering the quality of beam signal, and the existence of ping-pong effect, so as to reduce the number of times of beam reselection and position update, Effect of reducing power consumption and prolonging operating time
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Embodiment 1
[0029] Suppose the satellite terminal is covered by 3 beams at the same time, such as figure 2 As shown, the beam center points of the three beams are respectively recorded as beam center point 1, beam center point 2, beam center point 3, L 1 , L 2 and L 3 are the distances between the satellite terminal and beam center point 1, beam center point 2, and beam center point 3, which can be calculated by the following formula:
[0030]
[0031] Among them, i=1,2,3, R is the radius of the earth, α u , are the longitude coordinates of the satellite terminal and the beam center point i, respectively, β u , are the latitude coordinates of the satellite terminal and the beam center point i, respectively.
[0032] Then, for L 1 , L 2 and L 3 For comparison, let's say L 1 minimum, and L 2 and L 3 are greater than L 1 +ΔL, the satellite terminal selects beam 1 for camping, and then performs the normal location update process.
Embodiment 2
[0034] Suppose the satellite terminal is covered by 3 beams at the same time, such as image 3 As shown, the distance L between the satellite terminal and the beam center point 1, the beam center point 2 and the beam center point 3 1 , L 2 and L 3 Medium L 1 Minimum, L 2 Satisfy L 2 ≤L 1 +ΔL condition.
[0035] The satellite terminal obtains its own motion direction from the integrated angular accelerometer and accelerometer, that is, the angle θ between the velocity vector and true northu , calculate the angle θ between the satellite terminal and the beam center point 1, the beam center point 2 and the satellite terminal velocity vector 1 , θ 2 , calculated as follows:
[0036]
[0037] where m=1,2.
[0038] Subsequently, the satellite terminal compares θ 1 with theta 2 the size of. Suppose θ 2 1 , it can be considered that the satellite terminal will move for a longer time on the beam (beam 2) to which the beam center point with a small included angle belongs...
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