Inertial Navigation Utilizing Satellite Range and Doppler Observations.
NAVAL WEAPONS LAB DAHLGREN VA
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The application of linear estimation theory for the improvement of inertial navigation system estimates of aircraft position and velocity is described. The technique uses satellite range and range rate Doppler observations and vehicle borne altimeter measurements for the correction of inertial navigation system outputs and for the estimation of various other quantities such as frequency bias. Satellite orbit uncertainty is introduced into the solution through the mean anomaly uncertainty in each observed satellites computed orbit. A specific example is given which uses observations from two satellites. Author
- Air Navigation and Guidance