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焦面组件拼接完成后,要对焦面组件的设计和拼接指标进行测试,并开展温度试验和动力学环境试验,验证焦面组件各项指标的环境试验稳定性。
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对拼接完成的焦面组件静置,测试焦面组件的设计和拼接指标。
实测线阵CCD探测器的线视场为159.25 mm,拼接宽度为56 mm,满足设计指标要求。
拼接指标共面度检测的实测值见图11。拼接指标平行、共线度检测的实测值见图12。
图11和图12测试数据表明,焦面组件的CCD探测器的搭接116个像元,误差优于±2.5 μm,共线、平行度指标优于±2 μm,共面度指标优于±2.5 μm。
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为验证焦面组件的抵抗力、热环境能力,对焦面组件开展动力学试验和高低温循环试验[13-15]。图13为焦面组件开展动力学实验,表1和表2为力学振动试验的试验条件。图14为焦面组件开展高低温循环试验,表3为焦面组件开展高低温循环试验的试验条件。
表 1 焦面组件正弦振动试验条件
Table 1. Sine vibration test condition of the focal plane component
Direction x y z Parameters Frequency/Hz Magnitude Frequency/Hz Magnitude Frequency/Hz Magnitude 5-18 5.36 mm(O-P) 5-20 6.21 mm(O-P) 5-15 6.62 mm(O-P) 18-80 7 g 20-60 10 g 15-60 6 g 80-100 10 g 60-100 8 g 60-100 10 g Scan frequency 2 oct/min 表 2 焦面组件随机振动试验条件
Table 2. Random vibration test condition of the focal plane component
Direction x y z Parameters Frequency/Hz Magnitude Frequency/Hz Magnitude Frequency/Hz Magnitude 20-100 +6 dB/oct 20-100 +6 dB/oct 20-100 +6 dB/oct 100-240 0.06 g2/Hz 100-200 0.07 g2/Hz 100-180 0.06 g2/Hz 240-360 0.03 g2/Hz 200-330 0.03 g2/Hz 180-320 0.03 g2/Hz 360-500 0.06 g2/Hz 330-500 0.07 g2/Hz 320-500 0.06 g2/Hz 500-2 000 −12 dB/oct 500-2 000 −12 dB/oct 500-800 −12 dB/oct 250-300 1e-5 g2/Hz 250-300 1e-5 g2/Hz 800-1 000 0.001 g2/Hz 1000-2 000 −12 dB/oct 200-280 1e-5 g2/Hz Total rms acceleration/grms 5.52 g 5.93 g 4.93 g Testing time/min 2 综上,焦面组件基频是135 Hz,具有足够的动态刚度;在经历动力学、热学试验后,焦面组件的搭接精度、共面度,平行度和共线度指标基本没有变化,分别满足优于±2 μm、±2.5 μm和±2 μm的指标要求,具有极高的稳定性。
图 14 焦面组件高低温循环试验
Figure 14. Temperature cycle test with high and low temperature of focal plane component
表 3 焦面组件高低温循环试验条件
Table 3. High and low temperature cycle test condition of the focal plane component
Parameter Test conditions Note Temperature range −40−+75 ℃ Rate of temperature range ≥5 ℃/min Temperature tolerance High temperature 0−+4 ℃ Low temperature −4−0 ℃ Cycle index 2.5 One cycle:4 h,including 1.5 h staying at high temperature,2 h staying at low temperature
Design of focal plane assembly of linear array and area array detector based on one substrate of space remote sensor
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摘要: 空间遥感器的焦面组件是空间遥感器的一个关键部组件,完成光信号到电信号的转变功能,要求其具有高拼接精度、高稳定性和高度轻量化的性能。针对某深空探测遥感器兼具推扫成像和凝视成像的功能需求,设计了一种线阵面阵探测器共基板的焦面组件,主要包括焦面基板、CCD组件、CMOS组件和视频处理电路板等。通过合理的布局,在一块焦面基板上完成了三片CCD芯片和两片CMOS芯片的布局设计,结构紧凑,散热效果好,同时利用铜片分割和电箱结构覆盖的手段提升了焦面组件的电测兼容性能。完成焦面组件的拼接,CCD探测器的搭接误差优于±2 μm,各个探测器的共线和平行度误差优于±2 μm,共面度误差优于±2.5 μm。最终,对焦面组件开展了力、热环境试验,探测器的共线、平行度和共面度误差均无变化,表明焦面组件具有足够高的拼接精度和稳定性,焦面组件的基频为135 Hz,具有足够高的动态刚度,同时,还对整机进行了电磁兼容试验,性能良好。Abstract: Focal plane assembly of space remote sensor is a key component of space remote sensor, which is used to finish the transition function of the light signal into electrical signal. The focal plane assembly should have the characteristics of high splicing accuracy, high stability and high lightweight performance. In view of the function requirement of a deep space remote sensor with push-scan imaging and staring imaging, a focal plane assembly whose substrate was common with CCD detector and CMOS detector was designed, the focal plane assembly included focal plane substrate, CCD component, CMOS component, video processing circuit board, and so on. With a reasonable layout, the focal plane assembly was designed with three pieces of CCD and two pieces of CMOS, which was a compact structure and had a good heat dissipation effect. Moreover, the electromagnetic compatibility performance of focal plane assembly was improved obviously with the means of copper segment and box structure covering. After the assembling of focal plane assembly, the lapping error of CCD detector was better than ±2 μm, the collinearity and parallelism error of detector of CCD and CMOS was better than ±2 μm, the coplanarity error was better than ±2.5 μm. Finally, the force and thermal tests were carried out for the focal plane assembly, and the collinearity, parallelism and coplanarity errors of the detector did not change, indicating that the focal plane component has high enough splicage accuracy and stability. The fundamental frequency of the focal plane assembly is 135 Hz, which had sufficient dynamic stiffness. At the same time, the electromagnetic compatibility test was carried out on the space remote sensor, with good performance.
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表 1 焦面组件正弦振动试验条件
Table 1. Sine vibration test condition of the focal plane component
Direction x y z Parameters Frequency/Hz Magnitude Frequency/Hz Magnitude Frequency/Hz Magnitude 5-18 5.36 mm(O-P) 5-20 6.21 mm(O-P) 5-15 6.62 mm(O-P) 18-80 7 g 20-60 10 g 15-60 6 g 80-100 10 g 60-100 8 g 60-100 10 g Scan frequency 2 oct/min 表 2 焦面组件随机振动试验条件
Table 2. Random vibration test condition of the focal plane component
Direction x y z Parameters Frequency/Hz Magnitude Frequency/Hz Magnitude Frequency/Hz Magnitude 20-100 +6 dB/oct 20-100 +6 dB/oct 20-100 +6 dB/oct 100-240 0.06 g2/Hz 100-200 0.07 g2/Hz 100-180 0.06 g2/Hz 240-360 0.03 g2/Hz 200-330 0.03 g2/Hz 180-320 0.03 g2/Hz 360-500 0.06 g2/Hz 330-500 0.07 g2/Hz 320-500 0.06 g2/Hz 500-2 000 −12 dB/oct 500-2 000 −12 dB/oct 500-800 −12 dB/oct 250-300 1e-5 g2/Hz 250-300 1e-5 g2/Hz 800-1 000 0.001 g2/Hz 1000-2 000 −12 dB/oct 200-280 1e-5 g2/Hz Total rms acceleration/grms 5.52 g 5.93 g 4.93 g Testing time/min 2 表 3 焦面组件高低温循环试验条件
Table 3. High and low temperature cycle test condition of the focal plane component
Parameter Test conditions Note Temperature range −40−+75 ℃ Rate of temperature range ≥5 ℃/min Temperature tolerance High temperature 0−+4 ℃ Low temperature −4−0 ℃ Cycle index 2.5 One cycle:4 h,including 1.5 h staying at high temperature,2 h staying at low temperature -
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