In-orbit intersatellite laser communication experiment based on compound-axis tracking

Hanghua Yu; Shaowen Lu; Qiong Hu; Yongbo Fan; Funan Zhu; Haowei Xia; Jiawei Li; Jianfeng Sun; Xia Hou; Weibiao Chen; Huijie Liu

doi:10.3788/COL202523.040605

Chinese Optics Letters, Volume. 23, Issue 4, 040605(2025)

In-orbit intersatellite laser communication experiment based on compound-axis tracking

Hanghua Yu^1,3, Shaowen Lu^2、*, Qiong Hu², Yongbo Fan², Funan Zhu², Haowei Xia², Jiawei Li², Jianfeng Sun^2,3, Xia Hou^2,3, Weibiao Chen^2,3, and Huijie Liu^1,3

Author Affiliations

¹Innovation Academy for Microsatellites of Chinese Academy of Sciences, Shanghai 201203, China

²Shanghai Institute of Optics and Fine Mechanics, Chinese Academy of Sciences, Shanghai 201800, China

³University of Chinese Academy of Sciences, Beijing 10049, China

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Figures & Tables(13)

Fig. 1. Structure of the laser communication terminal.

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Fig. 2. Interpolation algorithm errors of position (a) and velocity (b).

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Fig. 3. Simulated attitude angular velocity and attitude interpolation error with Δt = 1.

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Fig. 4. Relationship between the terminal communication margin and the inter-satellite distance.

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Fig. 5. Schematic diagram of the beam pointing closed-loop control.

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Fig. 6. Bode diagram of (a) the closed-loop transfer function and (b) the vibration spectrum.

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Fig. 7. Relation of BER to the received power.

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Fig. 8. System test photograph. Satellite installation photograph (left) and ground test photograph (right).

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Fig. 9. Tracking efficiency with disturbance frequency.

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Fig. 10. Tracking error of the double satellite terminal.

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Fig. 11. BERs of the double satellite terminal with and without RS decoding.

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Table 1. Main Parameters of the Linkage

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Table 1. Main Parameters of the Linkage

Parameter	Value
Optical power	0.5 W
Wavelength	1559.79 nm
Divergence	60 µrad
Transmitting efficiency	95%
Tracking error	8 µrad
Receiving aperture	80 mm
Receiving efficiency	95%
Splitting ratio	96%
Coupling loss	−4.8 dB
Wavefront error loss	−0.8 dB
Communication sensitivity	−40.5 dBm

Table 2. Main Parameters of the Communication

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Table 2. Main Parameters of the Communication

Parameter	Value	Noise term	Function
Boltzmann coefficient k_B	1.38 × 10^-23 J/K	σ_Th	$\frac{4 K_{B} T}{R_{L}} B_{e}$
Temperature T	300 K	σ_Th	$\frac{4 K_{B} T}{R_{L}} B_{e}$
Resistance R_L	6.8 × 10³ Ω	σ_Shot−s	2eRGP_inB_e
Electrical bandwidth B_e	8.5 × 10⁹ Hz	σ_Shot−s	2eRGP_inB_e
Optical bandwidth B_o	10¹¹ Hz	σ_Shot−ASE	2eRS_ASEB_eB_o
Input power P_in	−42–−35 dBm	σ_Shot−ASE	2eRS_ASEB_eB_o
EDFA gain G	30.5 dBm	σ_S−ASE	4R²GP_inS_ASEB_e
Electron charge e	1.6 × 10^-19 C	σ_S−ASE	4R²GP_inS_ASEB_e
Detector response R	0.85 A/W	σ_ASE−ASE	R²S_ASE² (2B_o−B_e) B_e

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Hanghua Yu, Shaowen Lu, Qiong Hu, Yongbo Fan, Funan Zhu, Haowei Xia, Jiawei Li, Jianfeng Sun, Xia Hou, Weibiao Chen, Huijie Liu, "In-orbit intersatellite laser communication experiment based on compound-axis tracking," Chin. Opt. Lett. 23, 040605 (2025)

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