An on-orbit compensation method for Doppler effect in an inter-satellite self-homodyne coherent optical communication receiving system
A technology of coherent optical communication and Doppler effect, applied in the field of on-orbit parameter compensation, can solve problems such as increasing the complexity of the receiver, and achieve the effects of reducing the difficulty of development, avoiding automatic control loops, and simplifying complexity
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specific Embodiment approach 1
[0012] Specific implementation mode one: combine figure 1 and figure 2 This embodiment is described. The Doppler effect on-orbit compensation method of an inter-satellite self-homodyne coherent optical communication receiving system described in this embodiment includes the following steps:
[0013] Step 1. Calculate the frequency difference △f caused by the periodic change of Doppler frequency shift between satellites according to the orbit information of the satellite platform where the transmitter 1 is located and the orbit information of the satellite platform where the receiver 2 is located, and select the maximum value of the frequency difference △f as the maximum Frequency deviation △f max ;
[0014] Step 2. Calculate the communication bit rate R b and maximum frequency deviation △f max The ratio R b / △f max ;
[0015] Step 3, judging whether the ratio obtained in step 2 satisfies the condition for obtaining an uninterrupted laser communication link, and when th...
specific Embodiment approach 2
[0022] Specific implementation mode two: combination figure 1 and figure 2 Describe this embodiment. This embodiment is a further limitation of the Doppler effect on-orbit compensation method of an inter-satellite self-homodyne coherent optical communication receiving system described in Embodiment 1. In step 1, the maximum frequency deviation Δf max The method of obtaining is:
[0023] The distance L(t) between transmitter 1 and receiver 2 satisfies formula (1) and formula (2),
[0024] L(t 0 +τ 0 ) = L 0 +v(t 0 +τ 0 ) = cτ 0 (1)
[0025] L(t 0 +△t+τ 1 ) = L 0 +v(t 0 +△t+τ 1 ) = cτ 1 (2)
[0026] Among them, P 0 and P 1 are two points in the signal from transmitter 1,
[0027] P 0 at t = t 0 Time is sent from transmitter 1, after transmission time τ 0 After reaching receiver 2,
[0028] At the transmitter, P 1 with P 0 The time interval is △t,
[0029] P 1 Transit time τ 1 After reaching receiver 2,
[0030] L 0 is the distance between transmit...
specific Embodiment approach 3
[0043] Specific implementation mode three: combination figure 1 Describe this embodiment. This embodiment is a further limitation of the Doppler effect on-orbit compensation method of an inter-satellite self-homodyne coherent optical communication receiving system described in Embodiment 2. In step 3, an uninterrupted laser communication link is obtained. The road condition is R b / △f max ≥14.
[0044] The simulation results show that in order to make the communication bit error rate not higher than 10 in the whole laser link process -6 , so as to obtain an uninterrupted laser communication link, for super-Gaussian, Gaussian and FP optical filters, the required communication bit rate R b Respectively greater than 13.6△f max , 13.3△f max and 13△f max .
[0045] Therefore, the condition for obtaining an uninterrupted laser communication link is selected as R b / △f max ≥14. Judgment R b / △f max Whether it meets the conditions for obtaining an uninterrupted laser commu...
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