Simulation and Error Analysis of Spaceborne Carbon Monitoring with Supercontinuum Lidar

Hongyi Yin; Yiguo Pang; Ming Li; Shuang Gao; Longfei Tian; Denghui Hu; Guohua Liu

doi:10.3788/AOS241191

Acta Optica Sinica, Volume. 45, Issue 6, 0628009(2025)

Simulation and Error Analysis of Spaceborne Carbon Monitoring with Supercontinuum Lidar

Hongyi Yin^1,2, Yiguo Pang^1,2, Ming Li³, Shuang Gao¹, Longfei Tian¹, Denghui Hu¹, and Guohua Liu^1,2、*

Author Affiliations

¹Innovation Academy for Microsatellites of Chinese Academy of Sciences, Shanghai 201304, China

²University of Chinese Academy of Sciences, Beijing 100049, China

³Shanghai Institute of Technical Physics, Chinese Academy of Sciences, Shanghai 200083, China

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Figures & Tables(15)

Fig. 1. Overall schematic diagram for construction and evaluation of SC lidar model

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Fig. 2. Supercontinuum spectrum used in this study

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Fig. 3. Lunar reflectance based on ROLO model. (a) Lunar reflectance fit as an exponential function of phase angle g; (b) a full spectrum of lunar reflectance obtained through linear interpolation

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Fig. 4. Spectra of nighttime lights. (a) Normalized spectra of three typical light types; (b) characteristic nighttime lights radiance spectra of Las Vegas and Guangzhou

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Fig. 5. Simulation results of (a) SC lidar backscattered signal power, (b) solar background radiation power, and (c) lunar background radiation power under baseline condition

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Fig. 6. Impact of varied atmospheric parameters on SNR (1). (a) Atmosphere model; (b) SZA; (c) aerosol, day; (d) aerosol, night

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Fig. 7. Impact of varied atmospheric parameters on SNR (2). (a) Dark current density, day; (b) dark current density, night; (c) reflectance, day; (d) reflectance, night

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Fig. 8. Three selected absorption bands. (a) Band A, including O₂ absorption band 0.76 μm; (b) band B, including CO₂ absorption bands 1.57 μm, 1.61μm and CH₄ absorption band 1.64 μm; (c) band C, including CO₂ absorption bands 2.01 μm, 2.06 μm and CH₄ absorption band 2.3 μm

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Fig. 9. Maximum detecting altitude fit as a function of total peak power of SC lidar in baseline condition. (a) Band A (750~770 nm); (b) band B (1560~1750 nm); (c) band C (2000~2400 nm)

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Fig. 10. XCO₂ retrieval errors with varying SC lidar total peak power and dark current scenarios

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Table 1. Parameters of SC lidar used in this study

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Table 1. Parameters of SC lidar used in this study

Category	Parameter	Value
Laser transmitter^［18］	Spectral range /nm	400‒2400
	Total power /W	2
	Pulse duration /ns	1
	Repetition rate /MHz	20
	Total power stability /%	±1
	Divergence angle^［3］ /mrad	0.1
Telescope^［3］	Overall optical efficiency /%	70
Telescope^［3］	Diameter /m	1
Detector	Field of view （FOV）^［3］ /mrad	0.2
	Electronic bandwidth^［19］ /MHz	3
	Dark current density^［19］ /（fA/ $\sqrt[]{H z}$ ）	160
	Quantum efficiency^［19］ /%	80
	Internal gain^［20］	9
	Excess noise factor^［20］	3.2

Table 2. Percentile values of three selected regions
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Table 2. Percentile values of three selected regions
Region Percentile value
Max 1st 10th 50th 70th 100th
North China 749.7 39.3 4.1 0.7 0.5 0.0
East US 961.2 36.7 2.8 0.5 0.0 0.0
Xizang, China 172.6 0.8 0.0 0.0 0.0 0.0

Table 3. Spectral averaged derivatives of various current terms with respect to total noise current at an altitude of 120 km

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Table 3. Spectral averaged derivatives of various current terms with respect to total noise current at an altitude of 120 km

Time	Current term $x_{i}$	Expression	Spectral average value / $(A \cdot n m^{- 1})$	Spectral averaged derivative $\partial I_{N} / \partial x_{i}$
Day	Solar signal	$P_{s} (λ) M R$	$3.24 \times 10^{- 9}$	1.04
	Echo signal	$P_{r} (λ) M R$	$7.79 \times 10^{- 13}$	0.04
	Dark current	$i_{D} \sqrt[]{B}$	$2.77 \times 10^{- 10}$	0.73
Night	Lunar signal	$P_{m} (λ) M R$	$1.46 \times 10^{- 14}$	1.05
	Nighttime-light signal	$P_{N T L} (λ) M R$	$7.91 \times 10^{- 14}$	1.05
	Echo signal	$P_{r} (λ) M R$	$7.79 \times 10^{- 13}$	0.05
	Dark current	$i_{D} \sqrt[]{B}$	$2.77 \times 10^{- 10}$	0.99

Table 4. Minimum total peak power required for three bands assuming an orbital altitude of 500 km (daytime)

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Table 4. Minimum total peak power required for three bands assuming an orbital altitude of 500 km (daytime)

SNR threshold /dB	Minimum total peak power/ （10⁷ W）
	Band A			Band B			Band C
	30°	70°	89°	30°	70°	89°	30°	70°	89°
2	3.32	1.28	0.20	0.53	0.22	0.05	1.88	0.88	0.36
5	6.81	2.67	0.42	1.09	0.47	0.11	3.94	1.88	0.77
10	23.50	9.68	1.80	3.89	1.78	0.50	14.70	7.50	3.34

Table 5. Minimum total peak power required for three bands assuming an orbital altitude of 500 km (nighttime)
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Table 5. Minimum total peak power required for three bands assuming an orbital altitude of 500 km (nighttime)
SNR
threshold/dB
Minimum total peak power /（10⁶ W）
Band A Band B Band C
160 fA/ $\sqrt[]{H z}$ 20 fA/ $\sqrt[]{H z}$ 160 fA/ $\sqrt[]{H z}$ 20 fA/ $\sqrt[]{H z}$ 160 fA/ $\sqrt[]{H z}$ 20 fA/ $\sqrt[]{H z}$
2 1.37 0.30 0.46 0.10 3.46 0.73
5 3.04 0.94 1.01 0.32 7.51 2.29
10 13.40 8.38 4.52 2.82 32.60 20.50

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Hongyi Yin, Yiguo Pang, Ming Li, Shuang Gao, Longfei Tian, Denghui Hu, Guohua Liu. Simulation and Error Analysis of Spaceborne Carbon Monitoring with Supercontinuum Lidar[J]. Acta Optica Sinica, 2025, 45(6): 0628009

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Paper Information

Category: Remote Sensing and Sensors

Received: Jun. 20, 2024

Accepted: Sep. 29, 2024

Published Online: Mar. 17, 2025

The Author Email: Guohua Liu (liugh@microsate.com)

DOI:10.3788/AOS241191

CSTR:32393.14.AOS241191

Topics

laser devices and laser physics

Lasers and Laser Optics

Laser physics

laser manufacturing

Instrumentation, Measurement and Metrology

Table 1. Parameters of SC lidar used in this study

Table 1. Parameters of SC lidar used in this study

Table 2. Percentile values of three selected regions

Table 2. Percentile values of three selected regions

Table 3. Spectral averaged derivatives of various current terms with respect to total noise current at an altitude of 120 km

Table 3. Spectral averaged derivatives of various current terms with respect to total noise current at an altitude of 120 km

Table 4. Minimum total peak power required for three bands assuming an orbital altitude of 500 km (daytime)

Table 4. Minimum total peak power required for three bands assuming an orbital altitude of 500 km (daytime)

Table 5. Minimum total peak power required for three bands assuming an orbital altitude of 500 km (nighttime)

Table 5. Minimum total peak power required for three bands assuming an orbital altitude of 500 km (nighttime)