Maneuver Design for Fast Satellite Circumnavigation

Abstract

The feasibility of satellite operations in close proximity to a reference satellite is of interest for both civilian and military applications. One such operation is circular circumnavigation in a time period less than the orbital period of the reference satellite. This thesis investigates a guidance scheme for such maneuvers involving impulsive burns at specific points within a specified toroidal region centered on the circular-orbiting reference satellite. Two analytical methods for determining the magnitude and direction of the impulses are demonstrated. These methods are then used as initial estimates in an optimization scheme to produce the minimum total required impulse.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 2004
Accession Number
ADA424170

Entities

People

  • Stanley D. Straight

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Air Force Research Laboratories
  • Algorithms
  • Artificial Satellites
  • Astronautics
  • Coordinate Systems
  • Engineering
  • Equations
  • Flight Paths
  • Guidance
  • Maneuvers
  • Military Applications
  • Optimization
  • Orbits
  • Resident Space Objects
  • Space Objects
  • Spacecraft

Readers

  • Acoustics.
  • Calculus or Mathematical Analysis
  • Inertial Navigation Systems.

Technology Areas

  • Space
  • Space - Orbital Debris
  • Space - Spacecraft Maneuvers