Control of Formation Flying Satellites
Abstract
This report summarizes the work completed during the reporting period cited above. A technique for maintaining nominal separation distance between adjacent satellites in an elliptically orbiting constellation is developed and parametric trade-off studies performed. This technique is based on an initial impulsive-type correction of the daughter spacecraft at the first perigee in order to shift the direction of the line of apsides by a small angle. The technique works well in Keplerian orbits. In the presence of perturbations the results are critically dependent on the amplitude of the shift angle. Without subsequent corrections near collision situations can exist over the long term. Additional feedback type of correctional control is recommended to prevent unwanted secular drifts. Two types of feedback control strategies are considered here: an application of the linear quadratic regulator (LQR) theory based on errors in position, and also based on a Lyapunov function using osculating orbital elements. A preliminary deployment strategy is introduced based on near Hohmann-type of transfer orbits, and shows deployment can be achieved in one orbit.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 26, 2000
- Accession Number
- ADA378318
Entities
People
- Avaine Strong
- Peter M. Bainum
- Zhaozhi Tan
Organizations
- Howard University