The application of the classical boundary value problem (according to the Laplace principle) to primary orbit determination was investigated. Celestial bodies and satellites have in common that their motion is along conical orbits around a central mass. The additional problems for earth satellites is that the topocenter (observation station) does not move according to a conical trajectory. Methods were developed based on certain orbital hypotheses to solve the problem as a boundary value problem. Programs were produced for testing the proposed method for three given satellite orbits; results are reported.
Primary Satellite Orbit Determination from Laplace Angular Measurements Erstbahnbestimmung von Satelliten Aus Winkelmessungen Nach Laplace
1976
25 pages
Report
Keine Angabe
Englisch