Low Authority Control of Flexible Spacecraft via Numerical Optimization,
Abstract
For the design of low authority controllers for attitude control of flexible spacecraft a new method based on numerical optimization is presented. Thereby a dominant criterion to be optimized is determined, and the design requirements are formulated as constraints. Two different criteria are investigated: first a dissipation energy criterion is maximized and second a control energy criterion is minimized. The method is applied for attitude controller design of two models, the Drapper Model No. 1 and the Purdue Model. The first represents a flexible tetrahedral truss structure while the latter can be considered as model of a solar power satellite. Damping requirements for these models are formulated as design objectives and the controllers are determined using the proposed method. The achieved results show that due to the now existing efficient optimization software, controller design via numerical optimization is an useful and flexible tool for system design. This flexibility arises from the fact that arbitrary design criteria can be implemented. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1984
- Accession Number
- ADP003396
Entities
People
- G. Schulz