Integrated Dynamic Modeling and Ground Test Validation for Spacecraft Micro-Vibration Suppression Considering...

Area of Science:

• Spacecraft dynamics and control
• Optical payload performance
• Vibration engineering

Background:

• On-orbit micro-vibration significantly degrades space optical payload imaging and pointing accuracy.
• Existing research often isolates disturbance modeling, isolation design, or line-of-sight (LOS) stabilization, neglecting integrated analysis.

Purpose of the Study:

• To develop an integrated dynamic modeling methodology for spacecraft with optical payloads.
• To address the insufficiency in full-link dynamic modeling and analysis of micro-vibration.

Main Methods:

• Synergistic integration of disturbance identification, finite element modeling, model order reduction, and hybrid active-passive vibration isolation control.
• Fast steering mirror (FSM) regulation was incorporated.
• A full-spacecraft micro-vibration ground test with horizontal gravity unloading was performed for validation.

Main Results:

• Hybrid active-passive isolation achieved -30 dB attenuation, superior to passive isolation's -16 dB.
• Model validation showed excellent consistency with experimental data (acceleration error <7%, angular error <9%).
• Flywheels cause more LOS jitter than pumps due to time-varying disturbances and dispersed frequency energy.

Conclusions:

• The integrated dynamic model accurately predicts micro-vibration transmission and suppression.
• This provides a robust theoretical foundation for optimizing high-precision spacecraft system design.
• Effective micro-vibration mitigation is crucial for advanced space optical systems.