SPACE TRACK. SPACE VEHICLE EPHEMERIS AND DIFFERENTIAL CORRECTION PROGRAM UNIFIED THEORY

Abstract

An outline is given on the development of a differential correction theory for lunar and space probes. To overcome the singularities inherent in differential processes with conventional two-body descriptions of the path, as the eccentricity passes through unity in either the parabolic or rectilinear sense, a unified formulation of the two-body equations was developed. The differential correction procedure (over) is based upon an ephemeris, integrated in Encke form by special perturbations, and upon differential expressions derived from the unified two-body equations. The report includes experimentation with simulated range, range-rate, azimuth, altitude, right ascension and/or declination data to evaluate the performance of the resulting IBM 709 program.

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Document Details

Document Type
Technical Report
Publication Date
Jun 14, 1960
Accession Number
AD0248574

Tags

Communities of Interest

  • Air Platforms
  • C4I
  • Space

DTIC Thesaurus Topics

  • Air Force
  • Command And Control
  • Contracts
  • Earth Orbits
  • Ephemerides
  • Equations
  • Grids
  • Longitude
  • Lunar Probes
  • Lunar Trajectories
  • Observation
  • Orbits
  • Orientation (Direction)
  • Space Probes
  • Spacecraft
  • Trajectories
  • Vehicles

Readers

  • Calculus or Mathematical Analysis
  • Space Exploration and Orbital Mechanics.

Technology Areas

  • Space
  • Space - Orbital Debris