Real-time guidance for spacecraft reorientation using control moment gyroscopes

[摘要] Current research on large angle reorientation of spacecraft using control moment gyroscopes (CMGs) focuses on offline trajectory generation utilizing an open-loop guidance approach. This methodology leads to an increased sensitivity to uncertainty in the vehicle attitude, angular rate, and the CMG angular momentum. In order to increase the robustness to these uncertainties, a feedback guidance method is proposed utilizing linear model-predictive control theory to generate trajectory corrections in real-time. The feedback problem is solved as a system of linear equations using a pseudospectral discretization thus avoiding any explicit integration. The effectiveness of this approach is established by demonstrating the ability to improve the robustness of a nominal 90-degree rotation of the International Space Station using the onboard CMG system.

[发布机构] Rice University

[效力级别] materials