Research on Active Vibration Reduction Technology for Actively Supporting Main Mirror of Space Telescope

Zonghao Liu; Dongsheng Niu; Yu Ye

doi:10.3788/LOP240624

Laser & Optoelectronics Progress, Volume. 61, Issue 21, 2122003(2024)

Research on Active Vibration Reduction Technology for Actively Supporting Main Mirror of Space Telescope

Zonghao Liu^1,2,3, Dongsheng Niu^1,2、*, and Yu Ye^1,2

Author Affiliations

¹Nanjing Institute of Astronomical Optics and Technology, Chinese Academy of Sciences, Nanjing 210042, Jiangsu , China

²CAS Key Laboratory of Astronomical Optics and Technology, Nanjing Institute of Astronomical Optics and Technology, Nanjing 210042, Jiangsu , China

³University of Chinese Academy of Sciences, Beijing 100049, China

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Figures & Tables(14)

Fig. 1. Principle schematic diagram of permanent magnet spring force actuator

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Fig. 2. Open-loop output force variation response curve of permanent magnet spring force actuator

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Fig. 3. Closed-loop output force variation response curve of permanent magnet spring force actuator

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Fig. 4. Three-dimensional model of active vibration reduction system

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Fig. 5. Equivalent stress contour maps for harmonic response analysis. (a) Before active vibration reduction; (b) after active vibration reduction

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Fig. 6. Block diagram of active vibration reduction control system

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Fig. 7. Active vibration reduction system. (a) Active vibration reduction test platform; (b) physical diagram of active vibration reduction system

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Fig. 8. Response curves of active vibration reduction system. Convert force of acceleration sensor reading of (a1) 5 Hz 4 mm outer ring, (b1) 5 Hz 8 mm outer ring, (c1) 8 Hz 4 mm outer ring, (d1) 10 Hz 2.4 mm inner ring before active vibration reduction; comparasion of sensor force of (a2) 5 Hz 4 mm outer ring, (b2) 5 Hz 8 mm outer ring, (c2) 8 Hz 4 mm outer ring, (d2) 10 Hz 2.4 mm inner ring after active vibration reduction

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Table 1. Design indicators of permanent magnet spring force actuator
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Table 1. Design indicators of permanent magnet spring force actuator
Indicator Value range
Output force /N -100‒100
Motion range /mm -9.5025‒9.5025
Steady accuracy /N <0.05
Full range response time /s <1.5

Table 2. Relationship between number of motor pulse and output force of permanent magnet spring force actuator
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Table 2. Relationship between number of motor pulse and output force of permanent magnet spring force actuator
Number of motor pulse Force /N Number of motor pulse Force /N
580 -3.2 3480 -28.3
1160 -6.9 4060 -37.2
1740 -11.0 4640 -48.1
2320 -15.6 5220 -61.7
2900 -21.3 5800 -90.1

Table 3. Material properties of each component

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Table 3. Material properties of each component

Component	Density /（g·cm^-3）	Elastic modulus /GPa	Poisson’s ratio
Fused silica	2.53	90.3	0.24
Enclosure of strong permanent magnet （LY12）	2.78	73.1	0.33
Fixed support and base plate （Q235A）	7.85	200	0.3

Table 4. Natural frequencies of active vibration reduction system
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Table 4. Natural frequencies of active vibration reduction system
Modal order 1 2 3 4 5 6
Natural frequency /Hz 156.7 157.5 200.9 252.7 253.7 283.6

Table 5. Data comparison before and after active vibration reduction when vibration frequency is 5 Hz and amplitude is 8 mm
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Table 5. Data comparison before and after active vibration reduction when vibration frequency is 5 Hz and amplitude is 8 mm
Location Type Peak force /N Average force /N
Outer ring Before 35.4 34.0 34.0 32.7 34.1 34.0
After 17.7 18.2 17.2 16.2 16.0 17.1
Inner ring Before 34.5 33.7 33.3 34.0 33.9 33.9
After 16.8 16.4 16.0 16.6 17.8 16.7

Table 6. Vibration reduction effectiveness of active vibration reduction system
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Table 6. Vibration reduction effectiveness of active vibration reduction system
Experiment condition Vibration reduction effectiveness /%
Outer ring Inner ring
5 Hz 4 mm 49.4 50.7
5 Hz 8 mm 49.7 50.7
8 Hz 4 mm 49.5 53.1
10 Hz 2.4 mm 53.5 56.1

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Zonghao Liu, Dongsheng Niu, Yu Ye. Research on Active Vibration Reduction Technology for Actively Supporting Main Mirror of Space Telescope[J]. Laser & Optoelectronics Progress, 2024, 61(21): 2122003

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