High-speed free-space optical communication using standard fiber communication components without optical amplification

Hua-Ying Liu; Yao Zhang; Xiaoyi Liu; Luyi Sun; Pengfei Fan; Xiaohui Tian; Dong Pan; Mo Yuan; Zhijun Yin; Guilu Long; Shi-Ning Zhu; Zhenda Xie

doi:10.1117/1.APN.2.6.065001

Journals >Advanced Photonics Nexus >Volume 2 >Issue 6 >Page 065001 > Article

Advanced Photonics Nexus
Vol. 2, Issue 6, 065001 (2023)

High-speed free-space optical communication using standard fiber communication components without optical amplification

Hua-Ying Liu^1、†,*, Yao Zhang¹, Xiaoyi Liu¹, Luyi Sun¹, Pengfei Fan¹, Xiaohui Tian¹, Dong Pan², Mo Yuan³, Zhijun Yin³, Guilu Long², Shi-Ning Zhu¹, and Zhenda Xie^1、*

Author Affiliations

¹Nanjing University, College of Engineering and Applied Sciences, and Collaborative Innovation Center of Advanced Microstructures, School of Electronic Science and Engineering, School of Physics, National Laboratory of Solid State Microstructures, Nanjing, China

²Beijing Academy of Quantum Information Sciences, Beijing, China

³Xin Lian Technology Co., Ltd., Huzhou, China

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DOI: 10.1117/1.APN.2.6.065001 Cite this Article Set citation alerts

Hua-Ying Liu, Yao Zhang, Xiaoyi Liu, Luyi Sun, Pengfei Fan, Xiaohui Tian, Dong Pan, Mo Yuan, Zhijun Yin, Guilu Long, Shi-Ning Zhu, Zhenda Xie. High-speed free-space optical communication using standard fiber communication components without optical amplification[J]. Advanced Photonics Nexus, 2023, 2(6): 065001 Copy Citation Text

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$(a) Scheme of our FSO. (b) Picture of the 1 km experimental field. (c) Picture of the FSO devices. Alice is fixed in the building and Bob is loaded on an RCEV. (d) Diffraction loss of our FSO system. Red, diffraction loss only; blue, diffraction loss with loss of optics.$

Fig. 1. (a) Scheme of our FSO. (b) Picture of the 1 km experimental field. (c) Picture of the FSO devices. Alice is fixed in the building and Bob is loaded on an RCEV. (d) Diffraction loss of our FSO system. Red, diffraction loss only; blue, diffraction loss with loss of optics.

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(a) Design of FSO device. L, lens; IF, interference filter; DM, dichroic mirror; WDM, wavelength division multiplexer; TOSA, transmitter optical subassembly module; ROSA, receiver optical subassembly module; CMOS, complementary metal oxide semiconductor; BL, beacon laser; and FSM, fast steering mirror system (i=1,2). (b) Operation schematic of the APT system for acquisition, coarse tracking (left), and fine tracking (right).

Fig. 2. (a) Design of FSO device. L, lens; IF, interference filter; DM, dichroic mirror; WDM, wavelength division multiplexer; TOSA, transmitter optical subassembly module; ROSA, receiver optical subassembly module; CMOS, complementary metal oxide semiconductor; BL, beacon laser; and FSM, fast steering mirror system (

i = 1, 2

). (b) Operation schematic of the APT system for acquisition, coarse tracking (left), and fine tracking (right).

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Fig. 3. Performance of the APT system measured with 1 km separation. (a) Coarse tracking error. (b) Fine tracking error.

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Fig. 4. (a) Link loss for 1 km FSO. (b) Picture of the optical transceiver modules. (c) Communication bandwidth measurement for the module test and FSO. Red, direct connection test; blue, 1 km FSO test.

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Fig. 5. Link loss for 4 km FSO.

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Link type	Working distance	Transmission data rate	Optical amplification	Optical aperture	Weight	Size	Optical amplification	Power consumption	Tracking error	Link loss	Reference
Satellite-ground	400,000 km	622 Mbps (downlink)	Yes	100 mm (satellite) $4 \times$ 400 mm (ground)	30 kg	—	Yes	$\sim 90 W$	$10 μ rad$	—	Ref. 13
Airborne-ground	50 km	1.25 Gbps	Yes	600 mm (ground)	—	—	Yes	—	$20 μ rad$	45 dB (20 km) 56 dB (40 km)	Ref. 14
Airship-ship	20 km	1.5 Gbps	Yes	120 mm	—	—	Yes	—	$5 μ rad$	—	Ref. 8
Helicopter-helicopter	17.5 km	1.5 Gbps	Yes	120 mm	—	—	Yes	—	$6.2 μ rad$	—	Ref. 9
Fixed-wing aircraft-fixed-wing aircraft	136 to 144 km	2.5 Gbps	Yes	120 mm	—	—	Yes	—	$5.5 μ rad$	58.3 dB
Satellite-ground	450 km	50/100 Mbps	Yes	400 mm (ground)	2.3 kg (satellite)	$10 cm \times 10 cm \times 17 cm$ (satellite)	Yes	22 W(satellite)	$421 μ rad$	—	Ref. 15
UAV-ground	7 km	—	—	50 mm (UAV)	$\sim 8 kg$	—	—	—	$358 μ rad$ (azimuth)	—	Ref. 16
$617 μ rad$ (pitch)
Fixed end-RCEV	1 km	9.16 Gbps	No	90 mm	9.5 kg	$45 \times 40 \times 35 {cm}^{3}$	No	10 W	$3 μ rad$	13.7 dB	Our work

Table 1. Sample of performance of recent FSO systems.

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Component	Value
Coarse-tracking mechanism	Type	Three-axis motorized
Gimbal stage
Tracking range	Azimuth: $\pm 90 \deg$
Pitch: $\pm 60 \deg$
(With roll fixed)
Coarse-tracking sensor	Type	CMOS
FOV	0.04 rad * 0.04 rad
Size and frame rate	288 * 288 pixels and 1 kHz
BL0	Power	1 W
Wavelength	940 nm
Divergence	35 mrad
Fine-tracking mechanism	Type	FSM
Range	$\pm 212 μ rad$
Fine-tracking sensor	Type	CMOS
FOV	13 mrad * 10 mrad
Size and frame rate	288 * 288 pixels and 1 kHz
BL1	Power	5 mW
Wavelength	638 nm and 660 nm
Divergence	6 mrad
BL2	Power	5 mW
Wavelength	808 nm and 852 nm
Divergence	6 mrad