Accuracy of Interpolated and Differentiated Satellite Positions

Abstract

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).

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1974
Accession Number
ADA009233

Entities

People

  • Ted Sims

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Accuracy
  • Altitude
  • Artificial Satellites
  • Classification
  • Computers
  • Ephemerides
  • Equations
  • High Altitude
  • Interpolation
  • Intervals
  • Low Altitude
  • Medium Altitude
  • Orbital Elements
  • Orbits
  • Satellite Orbits
  • Standards
  • Trajectories

Readers

  • Astronomy and Astrophysics.
  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)
  • Systems Analysis and Design

Technology Areas

  • Space
  • Space - Orbital Debris
  • Space - Satellites