The Detumbling of an Axially Symmetric Satellite with an Orbital Maneuvering Vehicle by Nonlinear Feedback Control.
Abstract
The problem of detumbling a freely spinning and precessing axisymmetric satellite is considered. Detumbling is achieved with another axisymmetric orbital maneuvering vehicle (OMV) joined to the target satellite with a universal joint. The joint provides two rotational degrees of freedom and is translated across the surface of the OMV during the detumbling process. The target satellite and the OMV with its three momentum wheels are modelled as a five body system using Eulerian-based equations of motion developed by Hooker and Margulies. A Liapunov technique is applied to derive a nonlinear feedback control law which drives the system asymptotically to a final spin-stabilized state. State and control histories are presented and indicate that the detumbling process is benign. Constraint force and moment loads at the connection between the OMV and target satellites are also presented, and indicate that no extreme loads are encountered during the despinning and detumbling process. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 13, 1985
- Accession Number
- ADA163989
Entities
People
- Kirk R. Fleming
Organizations
- Air Force Institute of Technology