Discontinuous Low Thrust Orbit Transfer

Abstract

This paper examines the use of discontinuous low thrust for orbital transfers between two non-coplanar, circular orbits. The vehicle is assumed to be a solar-powered, ion rocket that cannot operate when it is within the earth's shadow. Two timescales are used to derive a minimum fuel trajectory. The fast timescale solution maximizes a change in inclination when given a change in semi-major axis for a single orbit. The slow timescale solution combines fast timescale results to obtain the minimum fuel trajectory. Results are presented for three specific transfers requiring varying amounts of shadow penetration. It is shown that the fuel penalty caused by discontinuous thrust is small. However, there can be a moderate increase in total trip time if the time within the shadow is large.

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1983
Accession Number
ADA136908

Entities

People

  • J. R. Cass Jr.

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Artificial Satellites
  • Circular Orbits
  • Classification
  • Electric Power
  • Electric Propulsion
  • Engineering
  • Equations
  • Flow Rate
  • Geometry
  • Mass Flow
  • Orbital Elements
  • Orbits
  • Schools
  • Security
  • Spacecraft
  • Trajectories

Readers

  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)
  • Space Exploration and Orbital Mechanics.

Technology Areas

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