| Type of Document |
Master's Thesis |
| Author |
Skelton II, Claude Eugene
|
| Author's Email Address |
cskelton@vt.edu |
| URN |
etd-12232003-100311 |
| Title |
Mixed Control Moment Gyro and Momentum Wheel Attitude Control Strategies |
| Degree |
Master of Science |
| Department |
Aerospace and Ocean Engineering |
| Advisory Committee |
| Advisor Name |
Title |
| Hall, Christopher D. |
Committee Chair |
| Lutze, Frederick H. Jr. |
Committee Member |
| Woolsey, Craig A. |
Committee Member |
|
| Keywords |
- spacecraft simulator
- control moment gyro
- momentum wheel
- attitude control
|
| Date of Defense |
2003-11-21 |
| Availability |
unrestricted |
Abstract
Attitude control laws that use control moment gyros (CMGs) and momentum wheels are derived with nonlinear techniques. The control laws command the CMGs to provide rapid angular acceleration and the momentum wheels to reject tracking and initial condition errors. Numerical simulations of derived control laws are compared. A trend analysis is performed to examine the benefits of the derived controllers. We describe the design of a CMG built using commercial off-the-shelf (COTS) equipment. A mixed attitude control strategy is implemented on the spacecraft simulator at Virginia Tech.
|
| Files |
| Filename |
Size |
Approximate Download Time
(Hours:Minutes:Seconds)
|
| 28.8 Modem |
56K Modem |
ISDN (64 Kb) |
ISDN (128 Kb) |
Higher-speed Access |
| |
CESIIetd.pdf |
4.24 Mb |
00:19:36 |
00:10:05 |
00:08:49 |
00:04:24 |
00:00:22 |
|
