Application of Semianalytic Satellite Theory to Maneuver Planning
Abstract
The high precision mean element (semianalytic) satellite theory developed at Draper Laboratory is more efficient than conventional numerical methods and more accurate than the current generation of analytic theories. This efficiency, along with its portability to a variety of computing environments makes the semianalytic theory a natural choice for maneuver planning applications. These applications will become more important in the future as the capability of individual platforms to maneuver, the number of platforms in space, and the requirements for rapid response to requests for data all increase. The application of semianalytic satellite theory to an Earth Observation satellite in an orbit similar to that expected for LANDSAT 6 is investigated. Orbit constraints such as sun synchronous, repeat ground track, frozen orbit, and non-impulsive maneuver capabilities are included in this analysis. Applications of maneuver planning to past and future satellite missions that include at least two of the listed orbit constraints are discussed. Since atmospheric drag is the primary uncertain disturbing acceleration to the nominal satellite orbit, upper and lower limits of a density confidence interval were determined. Two methods were analyzed; it was found that using forecast and actual solar flux and geomagnetic activity data from the years 1986-1990 resulted in a conservative but realistic confidence interval. The upper limit is utilized to compute the time of the orbit adjust burn and the lower limit of the density is used to calculate the magnitude of the orbit adjust burn. These limits are necessary so that the ground track boundaries are not exceeded.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1991
- Accession Number
- ADA239417
Entities
People
- Carole A. Jablonski
Organizations
- Air Force Institute of Technology