Accuracy of Interpolated and Differentiated Satellite Positions
NAVAL SURFACE WEAPONS CENTER DAHLGREN LAB VA DAHLGREN United States
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This study was undertaken to demonstrate the feasibility of storing just the position segment of the satellite ephemeris at maximum intervals of time. Position of the satellite at times not on the ephemeris would be found by interpolation. Satellite velocity and acceleration would be calculated via numerical differentiation of the positions. Partial derivatives of satellite velocity with respect to orbit parameters would be obtained from the numerical time derivatives of the position partials with respect to orbit parameters. Satellites at three specific altitudes were considered 1 a low altitude satellite 160 km, 2 a medium altitude 960 km, 3 a high altitude satellite 12000 km.
- Spacecraft Trajectories and Reentry