Description

• module doesn’t use reaction wheel - CMG (causes less vibrations potentially)

CMG (control moment gyroscope) causes micro vibrations in the satellite bus (main body). This leads to pointing jitter which affects the quality of images and the optical components. We must determine how we test the frequency of vibrations and how it affects the pointing accuracy. We must also determine the design of the damping mount.

2 main approaches to designing the damping mount

• Custom (but not really)
  • Research past satellite missions
  • Derive inspiration to determine how to mount the payload
• Off the shelf damping mounts
  • Frequency Analysis
  • Load Calculations
  • Damping Coefficient and Isolation Efficiency
  • Thermal and Material stress (Optional)
    • Determine if they meet the requirements (what are the requirements?)

Tasks

• [ ] Nareen: Research how to test pointing jitters (consider both simulation & physical testing)
• [ ] Joyce: Research whether OTS or custom design is more feasible.
• [ ] Sid: Trade study of OTS mounts based on performance, cost, and sizing requirements

Artifacts

Literature:

Research on Microvibrations Generated by a Control Moment Gyroscope on a Flexible Interface Based on a Dynamic Substructure Method

Notes

https://docs.google.com/document/d/1Y2sSFZWL-rV0KxRMXkEWJiLQynwLEN5fVcEVMNDjQYY/edit?usp=sharing