星载旋转部件间激光通信光传输装置设计与试验
doi: 10.11728/cjss2025.02.2024-0160 cstr: 32142.14.cjss.2024-0160
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谭嘉恒 男, 2000年9月出生于湖北省武汉市, 现于中国科学院大学(中国科学院长春光学精密机械与物理研究所)攻读博士学位, 主要研究方向为空间遥感器结构与机构. E-mail: tanjiaheng22@mails.ucas.ac.cn -
永强 男, 1995年出生于内蒙古通辽市, 现为中国科学院长春光学精密机械与物理研究所助理研究员, 主要从事航天器结构与机构, 航天器热控方向的研究工作. E-mail: yongqiang0220@126.com
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Design and Experiment of Optical Transmission Device for Laser Communication between Rotating Components on Satellite
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摘要: 针对旋转成像的超大幅宽空间相机与卫星平台间进行大容量、高可靠数据传输的需求, 设计了一套采用激光通信的空间光传输装置, 对高精度光学检测及装调方案进行了研究. 通过在发射端和接收端各安装主份和备份两套准直器的方法提高装置的可靠性, 并设计多光路通道实现了两套准直器的相互备份. 同时, 提出了一个高精度装调方案完成了对准直器光轴的精确测量及装调. 利用有限元分析软件MSC.PATRAN对空间光传输装置进行模态分析, 并对装调完成的空间光传输装置进行了振动试验. 结果表明, 空间光传输装置发射端和接收端的一阶频率分别为264.25 Hz和434.35 Hz, 振动试验后收发准直器间最大光功率损耗为1.94 dB, 各基准面法线的空间角变化均在5″ 以内. 说明该空间光传输装置能够克服卫星发射时的复杂力学环境影响, 具有较高的装调精度和可靠性, 可以满足星载旋转部件间激光通信数据传输的要求.Abstract: Aiming to address the demand for high-capacity and high-reliability data transmission between a rotating imaging ultra-wide-field space camera and the satellite platform, a space optical transmission device based on laser communication was designed, and the high-precision optical testing and alignment scheme was studied. The device’s reliability was enhanced by installing the primary and backup collimators at both the transmitter and the receiver, with mutual backup achieved through the design of multiple optical channels. At the same time, a high-precision alignment scheme to ensure accurate measurement and alignment of the collimator’s optical axis was proposed. Finally, the modal analysis of the space optical transmission device was carried out by using the finite element analysis software MSC.PATRAN and the vibration test of the installed space optical transmission device was completed. The results show that the first-order frequency of the transmitter of the space optical transmission device is 264.25 Hz, and the first-order frequency of the receiver is 434.35 Hz. After the vibration test, the maximum optical power penalty between the transceiver collimator is 1.94 dB, and the spatial angle change of each prism reference surface normal is within 5". It shows that the space optical transmission device can overcome the influence of a complex mechanical environment during the satellite launch, has high alignment precision and reliability, and meets the requirements of laser communication data transmission between satellite-borne rotating components.
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图 1 空间光传输装置与卫星安装位置
Figure 1. Position of the space optical transmission device on the satellite
图 5 45°反射镜角度偏差测量原理
Figure 5. Measurement principles of 45° reflector angular deviation
图 6 利用光纤环形器测准直器光轴的工作原理
Figure 6. Working principle of using fiber optic circulator to measure the collimator optical axis
图 8 发射端主备份准直器径向位置偏移测量过程
Figure 8. Radial position offset measurement process of the primary and backup collimators at the transmitter
图 9 发射端和接收端与旋转关节的装调误差
Figure 9. Alignment errors of the transmitter and receiver with the rotating joint
图 10 发射端前四阶模态振型. (a)一阶, (b)二阶, (c)三阶, (d)四阶
Figure 10. The first 4 order mode shapes of the transmitter. (a) 1st order, (b) 2nd order, (c) 3rd order, (d) 4th order
图 11 接收端前四阶模态振型. (a)一阶, (b)二阶, (c)三阶, (d)四阶
Figure 11. The first 4 order mode shapes of the receiver. (a) 1st order, (b) 2nd order, (c) 3rd order, (d) 4th order
表 1 空间光传输装置多光路通道组成
Table 1. Multiple optical channel composition of the space optical transmission device
Channel mode Transmitter working collimator Receiver working collimator 1 Primary collimator Primary collimator 2 Backup collimator Primary collimator 3 Primary collimator Backup collimator 4 Backup collimator Backup collimator 
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表 2 蜗轮蜗杆主要参数
Table 2. Main parameters of the worm gears
Object Parameter Object Parameter Modulus 1 Number of threads of worm 1 Reference circle diameter of worm 18 mm Lead angle 3.17983° Reference circle diameter of worm gear 40 mm Pressure angle 20°
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表 3 各组件材料参数
Table 3. Material parameters of each components
Component name Material name Density/(kg·m–3) Poisson ratio Elastic modulus/MPa Transmitter and receiver fixed bracket TC4 4440 0.34 106820 Linear guideway, lead screw 9 Cr18 7700 0.3 196000 Worm gear QSn4-3 8800 0.3 98686 Worm 40 Cr 7820 0.277 206780
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表 4 发射端和接收端前四阶模态频率
Table 4. The first 4 order modal frequencies of the transmitter and receiver
Order Transmitter frequency/Hz Receiver frequency/Hz 1 274.57 402.84 2 276.54 441.48 3 459.38 459.02 4 476.74 568.43
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表 5 振动试验结果
Table 5. Vibration test results
Position Direction Fundamental
frequency/HzSinusoidal vibration Random vibration Control
amplitude/gResponse
amplitude/gControl RMS/g Response RMS/g Transmitter
systemx 517.94 6 8.2 7.3 14.5 y 264.25 6 8.4 7.3 10.5 z 271.88 6 8.4 7.2 11.3 Receiver
systemx 1939.01 6 8.4 7.3 14.1 y 434.35 6 7.9 7.3 11.9 z 455.07 6 8.0 7.2 11.9 注 g为重力加速度.
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表 6 激光器发射功率11 dBm下振动试验前后各工作模式光功率损耗
Table 6. Optical power penalty in each operating mode before and after vibration test at 11 dBm laser emission power
Channel mode Before vibration test After vibration test Optical power range during one full rotation/dBm Maximum loss /dB Optical power range during one full rotation/dBm Maximum loss /dB 1 10.07～10.25 0.93 9.80～10.05 1.20 2 9.70～10.00 1.30 9.41～9.76 1.59 3 9.70～10.01 1.30 9.38～10.07 1.62 4 9.50～9.80 1.50 9.06～9.74 1.94
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表 7 振动试验前后标定数据变化
Table 7. Changes in calibration data before and after vibration test
Measurement objects Calibration data Theodolite readings Change before and after vibration Direction y z Δy Δz Transmitter reference prism Before vibration $89^\circ 59'58''$ $89^\circ 59'59''$ $3''$ $2''$ After vibration $90^\circ 00'01''$ $90^\circ 00'01''$ Receiver reference prism Before vibration $89^\circ 59'57''$ $90^\circ 00'03''$ $3''$ $4''$ After vibration $90^\circ 00'00''$ $90^\circ 00'07''$
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