Acta Photonica Sinica, Volume. 54, Issue 2, 0254102(2025)
Modeling of Microvibration Mechanism of Drag-free Control System for Space Gravitational Wave Detection Satellites （Invited）
Figures & Tables(23)
Fig. 1. Simulation results of solar radiation pressure perturbation force
Fig. 4. Simulation results of fluctuation coupling disturbance in capacitive sensors
Fig. 8. Schematic diagram of the structure of the Tianqin-3 concept satellite
Fig. 11. Micro-vibration disturbance transmission model for satellite platform based on state space equations
Fig. 12. Block diagram of the integrated simulation of the drag-free system
Fig. 14. Simulation results of angular response of precision pointing mechanism under each working condition
Fig. 15. PSD plot of angular response of precision pointing mechanism under each working condition
Table 1. Satellite orbital parameters
View tableView in ArticleTable 1. Satellite orbital parameters
Semimajor axis/km Eccentricity Inclination/（°） Right ascension of the ascending node/（°） Argument of periapsis/（°） Initial trueanomaly/（°） 100 938.056 412 0.000 411 94.785 623 209.438 226 0.061 831 325.619 846
Table 2. Simulation parameters of residual gas damping force
View tableView in ArticleTable 2. Simulation parameters of residual gas damping force
Parameters Value Average intracavity pressure， pave 9.77×10-6 Pa Cross-sectional area in the direction of the test mass motion， SPM 0.002 5 mm2 Molecular mass of gas inside the cavity， m0 4.579×10-6 kg/mol Average temperature inside the cavity， Tave 300 K Direction of motion X+
Table 3. Magnetic field coupling perturbation simulation parameters
View tableView in ArticleTable 3. Magnetic field coupling perturbation simulation parameters
Parameters Value 10-6 19 600 kg/m3 1.26×10-6 N/A3 3×10-6 T/m 2.45 kg 2×10-8 Am2 0.298 05 m±3.464 μm
Table 5. Thermodynamic simulation parameters
View tableView in ArticleTable 5. Thermodynamic simulation parameters
Parameters Value Densities， ρ 1.75 g/cm3 Elastic modulus， E 337 GPa Poisson's ratio， μ 0.307 Absorptance， αAb 0.9 Emissivity， 0.85 Coefficient of thermal conductivity， κ 10 W/（m·K） Specific heat capacity， Cp 1.0 J/（kg·K） Coefficient of thermal expansion， Ψ 1×10-5 K Stefan-Boltzmann constant， σ 5.67×10-8 W/（m2·K4） Ambient temperature， T0 0 K
Table 6. Thrust of the microthruster parameters
View tableView in ArticleTable 6. Thrust of the microthruster parameters
Parameters Value Valve core mass， 2 g Electromagnetic proportional amplification factor， Kf 12 Coulomb friction force， Ff 7 N Spring stiffness， Kth 6 N/m Flow coefficient， Cd 0.68 Thrust range 0~10 mN Nozzle inlet diameter， D 0.112 mm Nozzle exit diameter， Do 0.5 mm Flow rate range 0~13.72 μg/s Nozzle exit gas velocity， Vcg 700 m/s Nozzle inlet pressure， 0.6 MPa Nozzle exit pressure， 1.98 Kpa Needle valve tip angle， αTE 30° Electromagnetic valve suction control accuracy 10 μN
Table 7. Satellite geometric parameters
View tableView in ArticleTable 7. Satellite geometric parameters
Parameters Value Satellite mass 1 050 kg Satellite body diameter 3 200 mm Satellite body altitude 840 mm Solar panel diameter 5 300 mm Telescope diameter 400 mm
Table 8. Non-zero modal analysis results
View tableView in ArticleTable 8. Non-zero modal analysis results
Modal order Natural frequency/Hz 7 14.53 8 15.17 9 19.89 10 21.27 11 23.75 12 24.21 13 26.44 14 30.38 15 31.84 16 32.45
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Zhenglin YANG, Qing LI, Shaolong DENG, Chen WANG, Zhaoguo ZHANG, Lei LIU, Caiwen MA. Modeling of Microvibration Mechanism of Drag-free Control System for Space Gravitational Wave Detection Satellites （Invited）[J]. Acta Photonica Sinica, 2025, 54(2): 0254102
Paper Information
Category: Special Issue for Precise Beam Pointing for Space Gravitational Wave Detection
Received: Dec. 11, 2024
Accepted: Feb. 11, 2025
Published Online: Mar. 25, 2025
The Author Email: WANG Chen (wangchen@opt.ac.cn)
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