Mixed Control Moment Gyro and Momentum Wheel Attitude Control Strategies

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.

Name thesis:degree_name

Master of Science

Level thesis:degree_level

masters

Discipline thesis:degree_discipline

Aerospace and Ocean Engineering

Department dc:contributor.department

Aerospace and Ocean Engineering

Grantor dc:publisher

Virginia Tech

Year dc:date.issued

2003

Author dc:creator

• Skelton, Claude Eugene II

Chair dc:contributor.committeechair

• Hall, Christopher D.

Committee members dc:contributor.committeemember

• Woolsey, Craig A.
• Lutze, Frederick H. Jr.

• momentum wheel
• control moment gyro
• spacecraft simulator
• attitude control

Statement dc:rights

• In Copyright

Licence dc:rights.uri

• http://rightsstatements.org/vocab/InC/1.0/

Dc Identifier Other

etd-12232003-100311

OAI identifier oai:identifier

oai:vtechworks.lib.vt.edu:10919/9677