The use of known landmark measurements along with an onboard attitude reference system for estimation of both the ephemeris and attitude of an earth orbiting satellite is discussed. Simulation results are presented which show that, although known landmarks alone do not provide sufficient information to bound the uncertainty in attitude and ephemeris, they are useful in combination with other navigation aids, such as star tracking, ground tracking, or satellite tracking. An extended Kalman filter is used for optimal estimation. The result of using a smoothing algorithm is also shown.
Use of known landmarks for satellite navigation
American Institute of Aeronautics and Astronautics, Guidance and Control Conference ; 1975 ; Boston, MA
1975-08-01
Conference paper
No indication
English