Design and implementation of a full-chain dynamic simulation system for space-based gravitational wave detection
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摘要:
针对空间引力波探测中传统静态噪声叠加方法未考虑多物理场与控制系统之间动态耦合、难以满足高保真度任务仿真需求的问题，本文提出并设计了一套空间引力波探测全链路动态仿真系统，建立了多物理场与控制系统之间的闭环反馈能力。该系统采用动态闭环架构，包含航天器多物理场仿真模块、全链路噪声仿真模块、无拖曳控制仿真模块及数据处理分析模块。其中，物理场状态基于控制作用后的航天器状态计算生成，噪声由物理场状态经全链路噪声模型映射生成。该系统实现了全链路噪声的物理源头追溯与动态仿真。仿真实验发现，可移动光学组件（MOSA）运动与燃料消耗引起的自引力加速度扰动在观测频段（0.1 mHz~1 Hz）内可达10−13 m·s−2· Hz−1/2量级以上，需通过高精度在轨测量与标定等方法进行补偿或扣除。所构建的系统能够捕捉静态模型忽略的动态耦合效应，为空间引力波探测的任务设计、噪声溯源与灵敏度评估提供高保真度仿真平台。
Abstract:To address the issue that traditional static noise superposition methods in space-based gravitational wave detection neglect the dynamic coupling between multi-physics fields and the control system, making it difficult to meet the requirements of high-fidelity mission simulations, it is proposed and designed that a full-chain dynamic simulation system for space-based gravitational wave detection, establishing closed-loop feedback capability between the multi-physics fields and the control system. The system adopts a dynamic closed-loop architecture, comprising a spacecraft multi-physics field simulation module, a full-chain noise simulation module, a drag-free control simulation module, and a data processing and analysis module. In this architecture, the physical field states are computed based on the spacecraft states after control, and noises are generated through full-chain noise models mapped from the physical field states. The system achieves physical source tracing and dynamic simulation of full-chain noises. Simulation experiments reveal that self-gravity acceleration disturbances induced by the motion of the Movable Optical Sub-Assembly (MOSA) and fuel consumption can reach 10−13 m·s−2· Hz−1/2 level in the observation frequency band（0.1 mHz-1 Hz）, necessitating compensation or subtraction through high-precision in-orbit measurement and calibration methods. The constructed system is capable of capturing dynamic coupling effects neglected by static models, thereby providing a high-fidelity simulation platform for mission design, noise source tracing and sensitivity evaluation in space-based gravitational wave detection.
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图 1 全链路仿真系统核心模块关系示意图
Figure 1. Core module relationship diagram of the full-chain simulation system
图 2 航天器多物理场仿真计算模块接口示意图
Figure 2. Interface diagram of the spacecraft multi-physics simulation module
图 10 总残余加速度噪声频域曲线
Figure 10. Frequency-domain curve of total residual acceleration noise
图 17 燃耗与MOSA运动引起的自引力实时计算示意图
Figure 17. Real-time self-gravity calculation schematic for fuel consumption and MOSA motion
图 18 不考虑燃料消耗与MOSA运动后的灵敏度仿真曲线
Figure 18. Sensitivity curve without considering fuel consumption and MOSA motion
表 1 系统初始化参数
Table 1. Initial parameters configuration
序号 参数名称 参数初值 单位 1. 航天器1轨道初始位置(J2000.0日心黄道惯性系) [ 23957187920.4373 ,147231689435.394 ,
−743327719.789878 ]m 2. 航天器1轨道初始速度(J2000.0日心黄道惯性系) [− 29456.6666347458 ,4946.21532689005 ,259.702466544323 ]m/s 3. 航天器2轨道初始位置(J2000.0日心黄道惯性系) [ 25656431536.5843 ,148250892153.976 ,1495414337.05697 ]m 4. 航天器2轨道初始速度(J2000.0日心黄道惯性系) [− 29179.5437631783 ,5049.83621726837 ,0.103103604679852 ]m/s 5. 航天器3轨道初始位置(J2000.0日心黄道惯性系) [ 26914335435.3447 ,146719986739.374 ,
−743338173.419257 ]m 6. 航天器3轨道初始速度(J2000.0日心黄道惯性系) [− 29405.7565753330 ,5240.56479108545 ,
−259.494463138804 ]m/s 7. 检验质量块质量 1.95 kg 8. 检验质量边长 0.046 m 9. 检验质量磁化率 3e-6 / 10. 检验质量剩磁矩 2e-8 A·m2 11. 检验质量残余电荷量 1.6022e-12 C 12. 检验质量与电极的间隙 0.004 m 13. 激光波长 1.064e-6 m 14. 外差频率 1.8e7 Hz 15. 外差干涉效率 0.7 / 16. 调制深度 0.53 / 17. 光纤温度稳定系数 1e-12 rad·K−1·m−1· Hz−1 18. 电缆温度稳定系数 7e-12 rad·K−1·m−1· Hz−1 19. 本地激光功率 0.00175 W 20. 航天器接收激光功率 1.77e-9 W 21. 检验质量接收激光功率 1e-4 W 22. 激光相对功率波动 1e-4 Hz−1/2 23. 星间测距误差 0.1 m 24. 时钟稳定性 4e-14 s·Hz−1/2 25. 出气因子 2.5 / 26. 残余气体质量 6.65e-27 kg 27. 残余气体压强 1e-6 pa 
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