Optimal Launch Time for a Discontinuous Low Thrust Orbit Transfer

Abstract

This thesis searches for the optimal launch time of a discontinuous, low thrust transfer between non-coplanar, circular orbits. The spacecraft is assumed to be solar-powered rocket that cannot provide thrust in the earth's shadow. Two time scales are used to calculate a minimum time trajectory. The fast timescale produces a control law which maximizes a change in orbital elements for a single orbit. The slow timescale incorporates the control law so that the final boundary conditions are met in minimum time. Minimum transfer times are determined between winter and summer. Keywords: Low thrust; Electric propulsion; Orbit transfer; Solar propulsion; Transfer trajectories. (jhd)

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1988
Accession Number
ADA202693

Entities

People

  • Jeffrey M. Mccann

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Boundaries
  • Circular Orbits
  • Classification
  • Earth Orbits
  • Electric Propulsion
  • Engineering
  • Equations
  • Orbital Elements
  • Orbits
  • Propulsion Systems
  • Solar Propulsion
  • Spacecraft
  • Thrust
  • Thrusters
  • Trajectories
  • Vehicles

Fields of Study

  • Physics

Readers

  • Fluid Dynamics.
  • Space Exploration and Orbital Mechanics.

Technology Areas

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