Escape Trajectories for Low Thrust Vehicles

Abstract

The escape parameters (time, range angle and position) are studied for achieving optimum escape missions using low-thrust vehicle. Results are compared with previously reported analytical and numerical calculations. The equations of motion in addition to Euler-Lagrange optimization equations were solved using an IBM 7090 Low-Thrust Digital Computer Program. Specific impulses were varied from 1,000 to 25,000 sec and electrical power outputs were varied from 100 KW to 100 MW. Planar orbits initially circular) were assumed. Results of the parametric investigation are presented both in tabular and graphical form. Analysis of generated escape data indicate that the analytical equations previously reported have deviations ranging from approximately -25 percent to 44 percent. Numerical results previously reported are in general agreement with this study.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1962
Accession Number
AD0286923

Entities

People

  • John J. Dell

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Angular Momentum
  • Artificial Satellites
  • Astronautics
  • Circular Orbits
  • Computer Programs
  • Computers
  • Coordinate Systems
  • Differential Equations
  • Electric Power
  • Electric Propulsion
  • Engineering
  • Engineers
  • Equations Of Motion
  • Jet Propulsion
  • Mechanical Engineering
  • Orbits
  • Payload
  • Propulsion Systems
  • Spacecraft

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Calculus or Mathematical Analysis
  • Combustion and Flow Dynamics.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster
  • Space - Orbital Debris
  • Space - Spacecraft Maneuvers