Predicting Line-of-Sight Conjunction between a Specific Satellite and Others.
Abstract
The feasibility of designing a computer model to determine conjunction times between a primary object and any other satellite is investigated. An analytical integration scheme, which includes first order perturbations due to atmospheric drag and earth oblateness, is developed to predict satellite position in an inertial frame. Using an ellipsoidal, rotating earth model, conjunction between the primary object and any other satellite is determined by analyzing the respective topocentric vectors. Computer time is reduced by introducing discard schemes which retain only satellites that are a possible conjunction risk. Comparison between the computer model and existing methods of determination indicates the model is not only efficient, but computation time is significantly reduced. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1973
- Accession Number
- AD0774388
Entities
People
- Lee A. Mietz
Organizations
- Air Force Institute of Technology