Equations of Powered Rocket Ascent and Orbit Trajectory

Abstract

Equations of rocket and satellite dynamics are obtained at various levels of approximation and make possible analyses of powered rocket ascent, orbit injection, and subsequent orbital motion. Rocket and satellite trajectory are specified by these equations, which include the effects of earth's rotation and curvature. Various analysis techniques are given, so that the investigator can choose the simplest one suited to his needs. In the process, material not readily available is presented, and some problems of ambiguity and inaccuracy in standard references are resolved. (Author)

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Document Details

Document Type
Technical Report
Publication Date
May 07, 1979
Accession Number
ADA069296

Entities

People

  • M. H. Reilly

Organizations

  • United States Naval Research Laboratory

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Forces
  • Altitude
  • Artificial Satellites
  • Centrifugal Force
  • Coordinate Systems
  • Dynamics
  • Elliptical Orbits
  • Equations
  • Equations Of Motion
  • Flight Paths
  • Grids
  • Launch Vehicles
  • Orbits
  • Rocket Trajectories
  • Solar Radiation
  • Spacecraft
  • Trajectories

Readers

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

Technology Areas

  • Space
  • Space - Orbital Debris