Interactions Between SAS-C Spacecraft Nutations and Spin-Rate Control System.
Abstract
The SAS-C spacecraft is stabilized by a momentum biased reaction wheel and passive nutation damper. A closed-loop low-speed spacecraft spin rate control system is included which uses a single-axis gyro and a variable speed range on the reaction wheel. Dynamic instability can result from interactions among the gyro, damper, and spacecraft dynamic unbalance that are aggravated by gyro angular misalignment, gyro error signals, and spacecraft nutations. This report presents analytic, eigenvector, and digital computer dynamical analyses of the coupled systems describing mechanisms for instability; bounds on gyro error signal, tilt, and spacecraft dynamic unbalance that ensure system stability; and expected spin rate control system performance.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1974
- Accession Number
- ADA006115
Entities
People
- B. E. Tossman
- D. L. Thayer
Organizations
- Johns Hopkins University Applied Physics Laboratory